| Entries |
| Document | Title | Date |
|---|
| 20080206047 | TURBINE STAGE IN A TURBOMACHINE - A turbine stage in a turbomachine comprising ring sectors ( | 08-28-2008 |
| 20080213087 | Pump for Liquids Under Positive Pressure - A pump for liquids at positive pressure, includes a pump chamber ( | 09-04-2008 |
| 20080219837 | FAN AND FAN FRAME THEREOF - A fan has a fan, an impeller and a motor. The impeller is disposed in the fan frame, and the motor is disposed in the fan frame for driving the impeller. The fan frame has a housing, a base and at least one connecting element. The housing has an inlet and an outlet, and the base is disposed in the housing and at the outlet. The connecting element is disposed between the housing and the base. The base has a first airflow guiding structure disposed on the circumference of the base. The housing has a second airflow guiding structure disposed on the inner circumference thereof and adjacent to the outlet. The first airflow guiding structure and the second airflow guiding structure are correspondingly disposed. | 09-11-2008 |
| 20080226444 | CASING ASSEMBLY - Provision of panels within casings can cause problems where retaining bolts require apertures in the casings, which in turn may reduce the structural strength of that casing. By providing a loose or snug fit ring placed within the casing and appropriate retainer elements secured to that ring which in turn appropriately presents panels it is possible to provide a casing assembly which avoids the necessity of drilling or otherwise forming holes in the casing which may reduce structural strength. The rings, retainers and the panels do not need to be mechanically fixed to the casing although where possible a ring may be secured through bolts in areas of the casing where structural strength is less important. Where there is no bolting between the ring and the casing then dam elements can be provided at each end of the assembly to prevent lateral axial movement and therefore retain panel position within the casing. | 09-18-2008 |
| 20080247868 | FAN AND IMPELLER THEREOF - A fan has an impeller, a motor and a frame. The impeller and the motor are disposed within the frame, and the motor is connected to the impeller and drives the impeller to rotate. The impeller includes a hub and an odd number of blade sets. The blade sets are disposed around the circumference of the hub. Bach blade set has a plurality of the blades, and the blades of each blade set can be the same or not. For example, the blades in each of the blade sets have different tilting angles, heights and/or lengths while the blades are connected with the hub. Or the blades in each of the blade sets have different curvatures, arc lengths, thicknesses, or side-view shapes. | 10-09-2008 |
| 20080260525 | Device For Supplying Pulse Width-Modulated Output Pulses For the Motor of a Fan - A device for supplying pulse width-modulated output pulses for the motor of a fan has an arithmetic unit and at least one final output stage. The arithmetic unit and the final output stage are disposed in a rod-shaped housing. A fan encompasses a device that is located in a rod-shaped housing and is used for supplying pulse width-modulated output pulses. | 10-23-2008 |
| 20080273969 | HYBRID WORM GAS TURBINE ENGINE - A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component. | 11-06-2008 |
| 20080292453 | FAN AND FRAME THEREOF - A fan includes a frame and an impeller. The frame includes a main body, a plurality of guiding elements and a motor base. The main body has an airflow inlet and an airflow outlet. The guiding elements are disposed in the main body and located at the airflow outlet, wherein each of the guiding elements includes an inclined part and an axial extended part, and the inclined par meets the axial extended part at an angle. The motor base connects to the main body. The impeller is disposed on the motor base for providing an airflow, wherein the guiding elements guide the airflow away from the fan. | 11-27-2008 |
| 20090003997 | VARIABLE SHAPE INLET SECTION FOR A NACELLE ASSEMBLY OF A GAS TURBINE ENGINE - A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the plurality of discrete sections is selectively adjustable between a first position and a second position to influence the adaptive structure of each of the plurality of discrete sections. | 01-01-2009 |
| 20090060726 | RETAINER FOR A TURBOCHARGER - Disclosed are retainers for a turbocharger. In one embodiment, the retainer includes a generally annular body that defines a bore and one or more channels. The bore is generally directed along a central axis of the body and can be configured to mate with a nose of a center housing of a turbocharger. The channels can be configured to accommodate vanes associated with a cartridge assembly of the turbocharger. One or more legs may extend from the retainer body and may be configured to mate with and locate the retainer relative to a cartridge assembly for the turbocharger. The retainer can also include a concave portion disposed around a perimeter of the body. The concave portion and the body may be together configured to act as a spring when the retainer is mechanically loaded in a direction having a component parallel to the central axis. Also disclosed are corresponding turbochargers. | 03-05-2009 |
| 20090068000 | COMPRESSOR - An air bleeding passage | 03-12-2009 |
| 20090081030 | BOLT ASSEMBLY FOR STEAM TURBINE ENGINES AND METHOD OF ASSEMBLING THE SAME - A method of assembling a turbine casing is provided. The method includes inserting a bolt assembly through a first opening defined generally vertically through a first flange extending from a first casing member, such that a portion of the bolt assembly extends a distance upward from an upper surface of the first casing flange and such that the bolt assembly is retained within the first opening. The method further includes positioning a second casing member including a second flange including a second opening defined therein against the first casing member such that a portion of the bolt assembly extends through the opening defined in the second casing flange. | 03-26-2009 |
| 20090116957 | Steam turbine with two steam chambers - A steam turbine with at least two steam chambers which are enclosed by a basically tubular casing and which are separated from each other by means of at least one partition which is arranged in the casing, is characterized according to the invention in that the partition is formed from at least two flat partial surfaces which are formed in an inclined manner relatively to each other. | 05-07-2009 |
| 20090123274 | SPLIT GEARBOX AND NACELLE ARRANGEMENT - A gas turbine engine is disclosed that includes at least first and second gearboxes rotationally coupled to at least one spool. Accessory drive components are mounted on and driven by the gearboxes. The accessory drive components include, for example, a fuel pump, a hydraulic pump, a generator, a lubrication pump, or a starter. The accessory drive components are split between the two gearboxes to reduce the diameter of the nacelle adjacent to each gearbox. | 05-14-2009 |
| 20090155060 | Integrated Fan with Pump and Heat Exchanger Cooling Capability - Disclosed is a compact and integrated fan, pump, and heat exchanger system where air-cooling is performed via the fan, liquid cooling is performed via a pump, and the drilled pump diffusers act as a heat exchanger. The pump has drilled diffusers through which liquid passes into the volute, the drilled diffusers are streamlined and thus act as fan stator blades. Hot liquid is centrifuged and carried inside the drilled diffusers while air flows around the outside surfaces of the drilled diffusers. A heat transfer occurs where heat transfers from the hot liquid into the air stream. | 06-18-2009 |
| 20090191051 | STACKABLE NACELLE FOR WIND TURBINES - A stackable nacelle for a wind turbine includes a first piece having a top wall and integral first side walls extending at a first obtuse angle from each edge of the top wall; and a second piece, for mating with the first piece, having a bottom wall and integral second side walls extending at a second obtuse angle from each edge of the bottom wall. | 07-30-2009 |
| 20090238685 | Disguised air displacement device - A body has a back and parallel front. The back of the body defines an air inlet and a peripheral air outlet is associated with the front. A body chamber between the back and the front is in fluid communication with the air inlet and the air outlet. A structurally prominent faceplate is on the body proximate to the peripheral air outlet and bears a transforming aesthetic overlay. An air displacement unit is formed of a plurality of blades rotatable in a plane parallel with the back and the front. The air displacement unit is substantially concealed within the body chamber and is configured to accept air from the air inlet and urge the air through the air outlet. | 09-24-2009 |
| 20090246007 | Casing treatment for axial compressors in a hub area - A fluid flow machine includes a flow path formed by a casing | 10-01-2009 |
| 20090269191 | GAS TRANSFER FOOT - The present invention includes a molten metal pump and associated components that enable gas to be released into a stream of molten metal. The gas may be released into the molten metal stream (preferably into the bottom of the stream) flowing through a passage. Such a stream may be within the pump discharge and/or within a metal-transfer conduit extending from the pump discharge. The gas is released by using a gas-transfer foot that is positioned next to and is preferably attachable to the pump base or to the metal-transfer conduit. Preferably, the conduit (and/or discharge) in which the gas is released comprises two sections: a first section having a first cross-sectional area and a second section downstream of the first section and having a second cross-sectional area, wherein the second cross sectional area is larger than the first cross-sectional area. Preferably, the gas is released into or near the second section so that the gas is released into an area of relatively lower pressure. | 10-29-2009 |
| 20090269192 | SUPPORT MEMBER FOR OPTIMIZING DYNAMIC LOAD DISTRIBUTION AND ATTENUATING VIBRATION - A support member for a compressor having a shell may include a hub receiving a load from the compressor, at least three spokes radially extending from the hub, and at least three attachment locations attaching the at least three spokes to the shell. The support member may further include at least one connecting portion extending between at least two of the at least three spokes to transmit a load between the at least two spokes, whereby the at least one connecting portion is spaced apart and separated from the shell. | 10-29-2009 |
| 20090274553 | REPAIRED INTERNAL HOLDING STRUCTURES FOR GAS TURBINE ENGINE CASES AND METHOD OF REPAIRING THE SAME - A method of repairing a case for a gas turbine engine includes identifying areas of damage on its internal holding structures in a gas turbine case, and utilizing cold metal transfer to deposit weld material to the internal holding structures. | 11-05-2009 |
| 20090324398 | DEVICE FOR CARRYING OUT AN INDUCTIVE LOW-FREQUENCY OR HIGH-FREQUENCY PRESSURE WELDING METHOD, COMPRISING AN INSULATOR LOCATED BETWEEN THE INDUCTOR AND THE COMPONENTS IN THE ZONE OF THE JOINT - A device for carrying out an inductive low-frequency or high-frequency pressure welding method for joining metallic components, in particular components of a gas turbine, having at least one generator and at least one inductor, wherein an insulator is situated at least partly between the inductor and the components, in the area of the sections that are to be joined of the components, the insulator being made of a material that, due to its specific properties, does not, or does not significantly, prevent the magnetic interaction between the inductor and the components that are to be joined, and the insulator being situated at a distance from the inductor and the components, and that the insulator is made of high-temperature-resistant quartz glass. | 12-31-2009 |
| 20100003128 | Combustor transition piece aft end cooling and related method - A transition duct for a gas turbine includes a tubular body having a forward end and an aft end; a plurality of cooling channels formed on an exterior surface of the tubular body at the aft end; a closure band surrounding the aft end, covering at least a portion of the cooling channels; and a seal attached to the closure band, surrounding the aft end of the tubular body. | 01-07-2010 |
| 20100003129 | Flow control redistribution to mitigate high cycle fatigue - The present invention provides a method operable to improve pressure recovery and/or distortion within engine inlet. This method involves providing a first fluid flow to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions. Such engine conditions may be associated with a natural blade frequency of the engine at a particular speed. Embodiments of the invention allow blade vibration problems associated with engine operation at particular speeds to be solved without adding damping or increasing blade strength to change the natural frequency of the blades, thereby reducing weight and improving engine performance. | 01-07-2010 |
| 20100054928 | GAS TURBINE TRANSITION DUCT APPARATUS - A gas turbine transition duct is provided comprising a generally tubular main body having first and second ends, the first end being adapted to be positioned adjacent to a combustor unit and the second end being adapted to be positioned adjacent to a turbine and a collar coupled to the main body second end. The collar may have upper, lower and side portions. At least one of the side portions may be provided with a notched section. | 03-04-2010 |
| 20100068044 | COMPRESSOR - A compressor which includes: an inner casing arranged so as to cover a rotor shaft; an outer casing arranged so as to cover the inner casing and forming a fluid flow path around the rotor shaft; and a plurality of struts mounted in the entrance of the fluid flow path and between the inner casing and the outer casing; in which the plurality of struts are arranged in a radial pattern centered on the rotor shaft, and the spacings between the adjacent struts in the circumferential direction of the rotor shaft are unequal. | 03-18-2010 |
| 20100074738 | BLOWER | 03-25-2010 |
| 20100074739 | PASSIVE BOUNDARY LAYER BLEED SYSTEM FOR NACELLE INLET AIRFLOW CONTROL - A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle. | 03-25-2010 |
| 20100086396 | DUAL INLET REGENERATIVE AIR PUMP - The present invention relates to a pump arrangement ( | 04-08-2010 |
| 20100104431 | COMBINED AXIAL AND TRANSVERSE CONSTRAINT AND ALIGNMENT SYSTEM AND METHOD FOR ROTARY MACHINES - A system for aligning a shell of a rotary machine with a standard along an axial centerline and a transverse centerline of the rotary machine includes a pair of generally L-shaped hooks on the shell; a generally T-shaped member comprising a base, a post, and a cross member provided to the standard; a pair of axial gib keys provided on opposing sides of the cross member, at least one of the axial gib keys configured to engage at least one of the L-shaped hooks and the other being configured to engage the shell; and a pair of transverse gib keys provided on opposing sides of the post, each transverse gib key configured to engage a respective L-shaped hook. | 04-29-2010 |
| 20100129208 | ASSEMBLED FAN FRAME - An assembled fan frame suitable for a case body includes a framework, a plurality of first assemblies, a back slab, and a plurality of second assemblies. The framework includes a fixing slab, a first side wall and a second side wall facing each other, and an accommodation space is defined to accommodate at least one fan module. The fixing slab has at least one first vent and a plurality of first assembling holes which are disposed around the first vent. The first assembly is disposed through the first assembling hole and fastens the fan module on the fixing slab. The back slab is vertically mounted on a surface of the case body and faces the fixing slab. The back slab includes at least one second vent and a plurality of second assembling holes. The second assembly is disposed through the second assembling hole and detachably fixes the framework on the back slab. | 05-27-2010 |
| 20100143107 | ASSEMBLY WITH TWO INDEXED PARTS - In one exemplary implementation, an assembly may include two indexed parts. A first part may have a void formed therein and an axis, with the void defining at least one rotational stop and at least one radial stop. A second part may have a projection that is received at least partially in the void when the first and second parts are assembled together. The projection may have at least one rotational abutment surface adapted to engage said at least one rotational stop to limit relative rotation between the first and second parts, and the projection having at least one radial abutment surface adapted to engage said at least one radial stop to limit relative radial movement between the first and second parts in a direction away from the axis. | 06-10-2010 |
| 20100158677 | AXIAL FLOW FAN - An axial flow fan includes a blade having a curved portion formed in the vicinity of a radially outer end portion positioned opposite to the base portion in the radial direction of the peripheral wall portion of the hub. The curved portion is convex in the rotation direction, concave in the direction opposite to the rotation direction, and extends along the radially outer end portion of the blade. The curved portion extends from a rear end edge of the blade, positioned on a side where one end of the base portion of the blade is positioned, and extends in the radial direction of the hub to the vicinity of a front end edge of the blade, positioned on a side where the other end of the base portion of the blade is positioned and extending in the radial direction. | 06-24-2010 |
| 20100183431 | REPAIR OF CASE FLANGE WITH BOLT HOLES - A method for repairing damaged bolt holes in a flange having a plurality of circumferentially spaced bolt holes therein, with each bolt hole defining a center axis and the flange defining an outer diameter edge. The method includes removing parent material of the flange in a first pattern, and metallurgically joining a replacement detail to the parent material of the flange a location where the parent material of the flange was removed in the first pattern. The first pattern is bounded by first, second, third and fourth points. The first point corresponds to the center axis of a first of the plurality of bolt holes, the second point corresponds to center axis of a second of the plurality of bolt holes, and the third and fourth points are defined at the outer diameter edge of the flange circumferentially spaced from each other. | 07-22-2010 |
| 20100183432 | NOSE DOME FOR A TURBOMACHINE ROTOR - A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped. | 07-22-2010 |
| 20100189552 | Fan assembly - A fan assembly | 07-29-2010 |
| 20100196149 | Apparatus and Method for Preventing Cracking of Turbine Engine Cases - A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case. | 08-05-2010 |
| 20100209234 | Method for producing a turbine housing and turbine housing - A housing for a thermal turbomachine is provided. The housing includes an inner layer and an outer layer. The inner layer is subjected to greater thermal loading and the outer layer is subjected to less thermal loading, the inner layer being made of a more heat resistant material than the outer layer. Further, a method for producing a housing for a thermal turbomachine is provided. | 08-19-2010 |
| 20100226763 | FAN ASSEMBLY - A bladeless fan assembly for creating an air current includes a nozzle mounted on a base. The nozzle comprises an interior passage and a mouth for receiving the air flow from the interior passage and through which the air flow is emitted from the fan assembly. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle is detachable from the base, which is preferably sized to be accommodated within the opening of the nozzle for transportation. | 09-09-2010 |
| 20100226764 | FAN - A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet. | 09-09-2010 |
| 20100232948 | Fan Housing - A fan housing includes a casing body, two air vents, an assembling portion, two supporting ribs and a side outlet. The air vents and assembling portion are formed in a base plate of the casing body. The assembling portion is surrounded by the air vents. The supporting ribs spaces out the air vents. A remaining portion of the base plate other than the air vents, the assembling portion and the supporting ribs being defined as a border that surrounds and adjoins the air vents, with each supporting rib linking the assembling portion and the border. A dividing line is defined in the base plate to divide the casing body into an output section close to the side outlet and a temporarily-staying section away from the side outlet by the dividing line, and each supporting rib is not completely within the output section. Consequently, turbulence in the output section is suppressed. | 09-16-2010 |
| 20100239416 | Wind Turbine Nacelle - A nacelle for a wind turbine, the nacelle having a first height in its installed position and a second height in its transported position, the first height being higher than the second height, comprising a bottom part having a bottom face and two opposite side faces defining a space and a width of the bottom part and a top part. In the transported position, the top part extends inside the width or outside the width in order to cover at least part of the space. The invention also relates to a transportation kit and a transport method. | 09-23-2010 |
| 20100247299 | HIGH PRESSURE CASING ACCESS COVER - A closure device for a compressor having at least one access opening, wherein the closure device includes a plug portion disposeable at least partially within and configured to substantially obstruct the at least one access opening, a head portion having a shoulder surface extending generally radially outwardly with respect to the plug portion, wherein the head portion is generally disposeable against an inner surface of the compressor and configured to maintain the plug portion disposed within the at least one access opening during compressor operation, and a retainer member having a bracket engageable with an outer surface of the compressor and a threaded rod extending between the bracket and the plug portion, wherein the retainer member is configured to retain the plug portion disposed within the at least one access opening. | 09-30-2010 |
| 20100247300 | REDUCING INTER-SEAL GAP IN GAS TURBINE - A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal. | 09-30-2010 |
| 20100247301 | Power converting device - A power converting device includes a main body having a heat producing part housed therein, a fan case having a cooling fan therein for cooling the heat producing part provided in the main body, and a housing portion in the main body which houses the fan case. The fan case and the housing portion are interconnected so that the fan case is pivotally attached to and detached from the housing portion. | 09-30-2010 |
| 20100247302 | WIND ENERGY SYSTEM - A method and system for harvesting wind energy. The system may include a wind turbine disposed subjacent to a roof assembly of building. A plurality of conduits are adjacent to and extending below the wind turbine, wherein each of the plurality of conduits defines a first portion and a second portion, wherein the first portion defines a larger cross-sectional area than the second portion. | 09-30-2010 |
| 20100260599 | ROTARY MACHINE - To reduce the size of a rotary machine and to provide a rotary machine in which it is possible to achieve an improvement in reliability and performance of the rotary machine. A first casing ( | 10-14-2010 |
| 20100284801 | Turbo machine blade | 11-11-2010 |
| 20100284802 | INFLATABLE WIND TURBINE - A wind turbine has an impeller surrounded by a shroud. The shroud is formed from inflatable components extending between two rigid structural members. When inflated, the shroud acts to increase the energy generated by the impeller. Under adverse wind conditions, the inflatable components can be deflated to reduce surface area and wind load on the turbine. | 11-11-2010 |
| 20100290899 | VEHICULAR TURBOCHARGER COMPONENTS - Metal plated organic polymer compositions are useful as vehicular turbochargers components. Such components may have lighter weight, and/or superior corrosion resistance, and/or be more easily fabricated than conventional turbocharger components. | 11-18-2010 |
| 20100290900 | HYDROPOWER SYSTEM WITH INCREASED POWER INPUT CHARACTERISTICS - A turbine system having a series of uprights or fingers disposed about the inner surface of a rotating ring having turbine blades disposed within the ring. As the turbine blades are motivated by water movement, the fingers or uprights cause increased power by increasing the flow characteristics of the turbine system. The uprights can be of a variety of lengths and may be directed toward the central hub of the turbine or pointed at angles to the hub. Alternatively, the uprights may be bent on the end or curved to create a vortex into the main turbine blades. | 11-18-2010 |
| 20100316492 | Cooling Structure For Gas Turbine Transition Duct - A transition duct for conveying hot combustion gas from a combustor to a turbine in a gas turbine engine. The transition duct includes a panel including a middle subpanel, an inner subpanel spaced from an inner side of the middle subpanel to form an inner plenum, and an outer subpanel spaced from an outer side of the middle subpanel to form an outer plenum. The outer subpanel includes a plurality of outer diffusion holes to meter cooling air into the outer plenum. The middle subpanel includes a plurality of effusion holes to allow cooling air to flow from the outer plenum to the inner plenum. The inner subpanel includes a plurality of film holes for passing a flow of cooling air from the inner plenum through the film holes into an axial gas flow path adjacent to the inner side of the inner subpanel. | 12-16-2010 |
| 20100329857 | Compact Fan - The present invention relates to a compact fan, comprising a fan wheel, in particular a radial fan wheel ( | 12-30-2010 |
| 20110002778 | GAS TURBINE HOUSING COMPONENT - A gas turbine housing component includes a wall structure including two adjacent wall parts and a connection arrangement arranged between adjacent edges of the two wall parts. The connection arrangement includes an elongated seal strip positioned along the wall part edges and bridging the distance between the wall part edges. | 01-06-2011 |
| 20110014037 | Axial-flow compressor with a flow pulse generator - Axial-flow compressor including, within a compressor casing ( | 01-20-2011 |
| 20110020117 | CASING STRUCTURE OF STEAM TURBINE - In a steam turbine according to a first embodiment, an outer casing | 01-27-2011 |
| 20110027075 | VENTILATION FAN - A ventilation fan includes a rotor holder rotating around a rotation axis, an impeller cup including a plurality of blades provided on an outer circumference thereof, and a base portion arranged to rotatably support the rotor holder through a bearing portion. The base portion includes an outer circumferential wall extending upwards in an axial direction from an outer circumferential edge portion thereof. A gap defining a labyrinth structure is provided between an upper end portion of the outer circumferential wall of the base portion and a lower end portion of an outer circumferential portion of the impeller cup. A lower end portion of a cylindrical portion is located axially lower than the upper end portion of the outer circumferential wall of the base portion. | 02-03-2011 |
| 20110033285 | ASSEMBLY FOR A STATOR STAGE OF A TURBOMACHINE, THE ASSEMBLY COMPRISING AN OUTER SHROUD AND AT LEAST ONE STATIONARY VANE - The invention relates to an assembly for a stator stage of a turbomachine, the assembly comprising:
| 02-10-2011 |
| 20110033286 | NACELLE FOR TURBOJET ENGINE - The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off. | 02-10-2011 |
| 20110038721 | FAN WITH DUST-RESISTANT COATING - A method of making a fan having one or more dust-resistant surfaces comprises the steps of: providing (S | 02-17-2011 |
| 20110044806 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly comprises a first casing portion for at least partially encasing one or more rotating aerofoil structures of a turbomachine and a second casing portion; the first casing portion being movable with respect to the second casing portion. One or more resilient elements are arranged so as to resist movement of the first casing portion with respect to the second casing portion. | 02-24-2011 |
| 20110052378 | SIDE CHANNEL COMPRESSOR - A side channel compressor for compressing a gas comprises a housing ( | 03-03-2011 |
| 20110052379 | METHOD FOR MONITORING A MIXTURE OF AT LEAST TWO COMPONENTS - Provided is a method and apparatus for monitoring a mixture of at least two components. Also provided is a rotor blade of a wind power installation, a gondola casing of a wind power installation and a wind power installation itself. To provide a method in which the composition of the mixture can be easily monitored without damaging the workpiece produced therefrom, a dye is added to each component, wherein added to each component is its own color which is different from that of the other components, and the mixture of those components is monitored colorimetrically. A gondola casing and/or a rotor blade is manufactured by using such a method to determine amounts of components to include in a material of which the gondola casing or rotor blade is to be made. | 03-03-2011 |
| 20110052380 | SECTORED DISTRIBUTOR FOR TURBOMACHINE - The invention relates to a sectored distributor ( | 03-03-2011 |
| 20110064567 | Impingement Baffle for a Gas Turbine Engine and Gas Turbine Engine - An impingement baffle for a gas turbine engine is provided. The impingement baffle is a one piece impingement ring with one opening and with fastening elements at both free ends of the impingement ring to enable the closing of the impingement ring. A gas turbine engine including at least one such an impingement baffle is also provided. | 03-17-2011 |
| 20110064568 | Fluid Pump - An apparatus for pumping or compressing a fluid, the apparatus comprising:
| 03-17-2011 |
| 20110085896 | CASING FOR A MOVING-BLADE WHEEL OF TURBOMACHINE - A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved. | 04-14-2011 |
| 20110085897 | CASING COMPRISING A PERIPHERAL SHROUD FOR A TURBOMACHINE ROTOR - The present invention relates to a casing ( | 04-14-2011 |
| 20110085898 | VERTICAL AXIS TURBINE FOILS - Geometries of foil shapes that act particularly well to increase the power output of adjacent vertical axis turbines are presented. | 04-14-2011 |
| 20110091315 | FAN WITH PRESSURIZING STRUCTURE - A fan with pressurizing structure includes a rotor having a main body, blades spaced on the main body, a magnetic body annularly mounted in the main body, and a shaft axially connected to an inner side of the main body; a frame having a sleeve and at least one bearing rotatably received in the sleeve, and an opposing end of the shaft being inserted into the bearing; a stator assembly fitted around the sleeve and including silicon steel plates and a base plate; and a plurality of first pressurizing sections selectively provided on one of the base plate and an end face of the magnetic body. With the first pressurizing sections, deposition of moisture and salt fog in the sleeve and the rotor can be prevented to avoid corroded and damaged bearing and rotor shaft, and the service life of the whole fan is increased. | 04-21-2011 |
| 20110091316 | FAN ASSEMBLY WITH SNAP-ON COVER - An exemplary fan assembly includes a fan and a snap-on cover. The fan includes a bracket and an impeller disposed in the bracket. The cover includes a base body, a number of first clasps extending outwardly from a first side of the base body, a number of retaining clasps extending outwardly from an opposite second side of the base body, and an operation portion connecting the retaining clasps. The base body is disposed on the bracket, the first clasps clasp a first side of the bracket, the retaining portions clasp an opposite second side of the bracket, and the operation portion presses the bracket. | 04-21-2011 |
| 20110103941 | BREATHER DUCT SHIELDING - A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is at least one clean air outlet bounding the exhaust port and arranged to expel, in use, a vortical flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port. | 05-05-2011 |
| 20110116913 | HYDRODYNAMIC TORQUE CONVERTER - The invention relates to a hydrodynamic torque converter having a pump shell including blades, a turbine shell including blades, a torus-shaped flow cycle. The blades are configured to be attached at the respective shells through inner walls and the inner walls of the turbine shell and of the pump shell form an inner torus with outer surfaces facing the flow cycle and an end of an extension of the inner wall of at least one shell and an end of an extension of an adjacent shell are disposed in a plane and extend over one another and define a gap between one another. A transition from the extensions is configured to be hydrodynamically smooth. | 05-19-2011 |
| 20110123319 | COMPOSITE SLIDER SEAL FOR TURBOJET PENETRATION - A seal assembly for a turbo machine, such as a turbo jet, includes a housing having a retainer secured relative to the housing. A seal is arranged between the housing and the retainer. The seal provides an opening configured to receive a penetrating element. The seal comprises a composite material. In one example, an anti-rotation feature prevents the seal from rotating relative to the housing. The anti-rotation feature includes a rivet received in a hole in the seal that cooperates with at least one of the housing and the retainer to maintain the seal in a desired angular position. | 05-26-2011 |
| 20110123320 | Arrangement with a Nacelle and with an Instrument - An arrangement with a nacelle and with at least one instrument of a wind turbine is disclosed. The instrument is connected with a rod. A channel penetrates the wall of the nacelle. The channel interacts with the rod in a way that the rod and its assigned instrument are moved through the channel between a first and a second position. The instrument is positioned inside the nacelle at the first position for installation and/or service purposes, while the instrument is positioned outside the nacelle at the second position for operation purposes of the instrument. | 05-26-2011 |
| 20110142605 | LOW-PRESSURE STEAM TURBINE HOOD AND INNER CASING SUPPORTED ON CURB FOUNDATION - A support arrangement for an exhaust hood. The inner casing in the inventive arrangement is supported directly by the curb foundation. As a result, the effect of pressure changes in the exhaust hood are eliminated and the effect of temperature changes of the exhaust hood are reduced relative to the positioning of the inner casing and the rotor within it. Shaft bearings may be outside the exhaust hood located in a standard directly on the foundation. Rotor end packing may also be attached to the standard. The exhaust hood can be a much simpler design with less structural supports and less fabrication time. Easier maintenance is facilitated because the shaft bearings are not tucked under the exhaust hood and the end packing can be removed without removal of a large section of the exhaust hood. | 06-16-2011 |
| 20110150638 | Fan Device - A fan device includes: a fan housing configured with a receiving space defined among opposite top and bottom walls, and a surrounding side wall; a fan impeller mounted in the receiving space, disposed adjacent to an air outlet in the top wall and operable to rotate about a central axis transverse to the top and bottom walls of the fan housing; and an air-guiding unit mounted fixedly in the receiving space and disposed adjacent to an air inlet in the bottom wall. The air-guiding unit includes a central connecting member disposed axially with the central axis, and a plurality of angularly spaced apart air-guiding blades interconnecting the central connecting member and the surrounding sidewall. An angular distance between each adjacent pair of the air-guiding blades is different from that of any other adjacent pair of the air-guiding blades. | 06-23-2011 |
| 20110150639 | Fan Device - A fan device includes: a fan housing configured with a receiving space defined among opposite top and bottom walls, and a surrounding side wall; and a fan impeller mounted in the receiving space, disposed adjacent to an air outlet in the top wall and operable to rotate about a central axis transverse to the top and bottom walls of the fan housing. The fan impeller includes a hub body disposed coaxially with the central axis, and a plurality of angularly spaced apart fan blades extending outwardly and radially from the hub body. An angular distance between each adjacent pair of the fan blades is different from that of any other adjacent pair of the fan blades. | 06-23-2011 |
| 20110158794 | INTERMEDIATE HOUSING FLOOR FOR A FLUID KINETIC MACHINE - An intermediate housing floor for a fluid kinetic machine is provided. The intermediate housing floor includes a partial joint at which the intermediate housing floor may be divided during installation and/or removal into/from the fluid kinetic machine and is made up of at least two overlapping partial joint surfaces at sections of the intermediate housing floor that face one another. A recess is provided in the area of the overlap in at least the one partial joint surface, a coating is kept in the recess. The coating protrudes from the one partial joint surface as a protrusion in the removed state of the intermediate housing floor in which the intermediate housing floor is divided at the partial joint so that in the installed state of the intermediate housing floor the coating abuts against the other partial joint surface facing the one partial joint surface, whereupon the partial joint is sealed. | 06-30-2011 |
| 20110164965 | STEAM TURBINE STATIONARY COMPONENT SEAL - A steam turbine and a seal member between stationary components of a steam turbine are disclosed. The seal member is annular, with a cross-section having an elongated seal member and bulbous ends that are adapted to be inserted into grooves in the stationary components to form point seals between the bulbous ends and axial faces of the grooves. The bulbous ends are designed to rotate with respect to the axial faces of the annular grooves and the elongated member is designed to flex to maintain the point seals in response to a realignment of the components. | 07-07-2011 |
| 20110164966 | Method and apparatus to improve wake flow and power production of wind and water turbines - A wake flow injector method and apparatus are presented to improve the power production of wind and water turbines by directly injecting higher-energy fluid or air directly into the wake flow region behind the rotor or turbine. | 07-07-2011 |
| 20110171014 | NACELLE COMPRISING AT LEAST ONE SURGE TRAP - The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure ( | 07-14-2011 |
| 20110176915 | BLADE FOR A WATER TURBINE - A turbine blade is described which includes a blade root;a blade tip; a leading edge extending from the blade root to the blade tip; a trailing edge extending from the blade root to the blade tip; a blade root chord defined as a straight line between the leading edge and the trailing edge at the blade root; a blade tip chord defined as a straight line between the leading edge and the trailing edge at the blade tip; wherein the blade tip chord is angularly displaced from the blade root chord by a twist angle of between 50° and 90°. | 07-21-2011 |
| 20110194930 | FAN HOUSING STRUCTURE - A fan housing structure including a base seat and a sideboard. The base seat has a bed section and a mating section extending along a periphery of the bed section. The bed section has a bush made of a material other than the material of the bed section. The bush is disposed on the bed section to axially protrude therefrom. The sideboard is made of a material other than the material of the base seat. The sideboard is disposed on the mating section and integrally connected with the base seat. The sideboard and the base seat together define a space therebetween. The sideboard and the bush are made of a material other than the material of the base seat and are integrally connected with the base seat by means of insert injection molding. Accordingly, the fan housing structure has enhanced structural strength and thinner thickness to save room. | 08-11-2011 |
| 20110200428 | WIND-DRIVEN ELECTRIC PLANT - A wind-driven electric plant comprises an inlet shell shaped as a circle and a circular outer shell with the cross section of its inside surface of a round form. Inside the circular shell, provision is made of a coaxially arranged turbine. Kinematically coupled with the turbine is a mechanism for the conversion of mechanical energy. At least a portion of the outer shell is ellipsoidal in cross section. The major axis of an ellipse defining the cross section of the outside surface of the inlet shell at an inlet of the latter is not less than 0.55 and not more than 0.95 of the dia. of a circle defining the inside surface of the outer shell in its minimum section. | 08-18-2011 |
| 20110206503 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED ACCORDING TO THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is hydroformed against a circular blank made from titanium or titanium alloy. | 08-25-2011 |
| 20110211942 | METHOD AND SYSTEM FOR A LEAKAGE CONTROLLED FAN HOUSING - A method and system for a fan assembly that includes a fan casing having a longitudinal centerline axis extending from an upstream inlet opening to a downstream outlet opening is provided. The fan assembly also includes a first substantially cylindrical casing segment extending circumferentially about and substantially axially aligned with tips of a plurality of blades extending from a rotor hub, the first casing segment including a first inner diameter that is greater than the rotor diameter, a second casing segment configured to extend axially in a direction opposite a flow of fluid through the fan casing, the second casing segment including a second inner diameter, the second inner diameter less than the first inner diameter and the rotor diameter, and a third casing segment including the first inner diameter along a first circumferential edge, the second inner diameter along a second circumferential edge, and a surface extending therebetween. | 09-01-2011 |
| 20110211943 | PANELLED ASSEMBLY - A panelled assembly has a spacer | 09-01-2011 |
| 20110211944 | AIR CONDITIONER - There is provided an air conditioner having a fan guard assembly which is easy to assemble, and the transversal crosspieces of the fan guard assembly are not easily disengaged from the longitudinal crosspieces. The air conditioner includes: an air conditioner, comprising: a housing accommodating therein an air delivery fan and having a discharge opening from which an airflow generated by the air delivery fan is blown out; and a fan guard assembly disposed between the air delivery fan and the discharge opening, in the housing, wherein the fan guard assembly includes a first member having a protruding portion protruding in such a manner as to form a retaining groove, and a second member held in the retaining groove of the first member; and the protruding portion protrudes in such a manner that, in a side view, the protruding portion intersects a rectilinear line passing a center point of the second member held by the retaining groove and an arbitrary point P | 09-01-2011 |
| 20110223012 | TURBINE ROTOR ASSEMBLY AND STEAM TURBINE - A turbine moving blade cascade | 09-15-2011 |
| 20110236194 | FAN APPARATUS WITH AIR DUCT - An air duct includes a cover and two adjusting pieces. The cover includes a top board and two end boards extending downwards from two opposite ends of the top board. The cover defines an air outlet in a front of the cover and an air intake in a rear of the cover. Two adjusting pieces are slantingly extended from rear ends of the two side boards toward the air outlet. | 09-29-2011 |
| 20110236195 | Compressor - It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. | 09-29-2011 |
| 20110243718 | REINFORCED FAN FRAME STRUCTURE - A reinforced fan frame structure includes a frame body and at least one metal ring. The frame body has a seat portion with a centered bearing cup axially forward extended from the seat portion. The metal ring is integrally associated with the seat portion and has an inner circumferential edge facing toward the bearing cup. With the metal ring integrally associated with the seat portion of the frame body, it is able to effectively control the deformation and the flatness of the seat portion and accordingly, effectively upgrade the overall structural strength of the seat portion. | 10-06-2011 |
| 20110243719 | NON-CIRCULAR AFT NACELLE COWLING GEOMETRY - A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section. | 10-06-2011 |
| 20110255959 | TURBINE ALIGNMENT CONTROL SYSTEM AND METHOD - A turbine that includes a rotor, an inner turbine shell, an outer turbine shell, and a sliding engagement between the inner turbine shell and the outer turbine shell. The inner turbine shell is a single piece construction that completely surrounds at least a portion of the rotor, and the outer turbine shell surrounds the inner turbine shell. A method for aligning turbine components that includes aligning a single-piece inner turbine shell substantially concentric with a rotor and surrounding the single-piece inner turbine shell with an outer turbine shell. The method further includes supporting the single-piece inner turbine shell with respect to the outer turbine shell using a bearing assembly between the single-piece inner turbine shell and the outer turbine shell. | 10-20-2011 |
| 20110268565 | Tunnel turbine system generates potential energy from dorment kinetic energy - A generator system includes a pipe line which includes a control valve for diverting input gas or liquid into a pair of bypass pipe lines, whose output is coupled with two nozzle venture inlets in a turbine housing. Gas or liquid entering the turbine housing through the nozzle venture inlets rotates a turbine impellor having a generator shaft to generate energy. Gas or liquid exiting from the turbine housing, along with diverted input gas or liquid, pass through an ejector device which eliminates back pressure and restores any pressure loss. | 11-03-2011 |
| 20110274537 | BLADE EXCITATION REDUCTION METHOD AND ARRANGEMENT - An impeller shroud is configured to receive an impeller. The impeller shroud establishes a plurality of air-bleed holes configured to communicate air with an impeller. The air-bleed holes are circumferentially distributed about the impeller shroud. The circumferential spacing between some adjacent air-bleed holes within the plurality of air-bleed holes is different than the circumferential spacing between other adjacent air-bleed holes within the plurality of air-bleed holes. A diffuser vane is configured to direct pressurized air to the combustor, the diffuser vanes are circumferentially distributed about the blade exducer. The circumferential spacing between some adjacent diffuser vanes within the plurality of diffuser vanes is different than the circumferential spacing between other adjacent diffuser vanes within the plurality of diffuser vanes. | 11-10-2011 |
| 20110299979 | Method for Improving the Stall Margin of an Axial Flow Compressor Using a Casing Treatment - A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method. | 12-08-2011 |
| 20110311354 | COMPRESSORS WITH CASING TREATMENTS IN GAS TURBINE ENGINES - A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove. | 12-22-2011 |
| 20110318173 | GUIDE SYSTEM FOR NACELLE ASSEMBLY - A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided. | 12-29-2011 |
| 20120003083 | Side Channel Pump for Conveying Fuel in a Motor Vehicle - A side channel pump for conveying fuel having a flow divider disposed in an impeller. The flow divider divides blade chambers of the impeller into individual partial chambers. Flow dividers are also disposed in housing parts opposing the impeller having partial ring-shaped channels radially encompassing each other. The flow dividers in the impeller and in the housing parts are at a distance from each other in order to allow cross flow between the conveyance chambers formed by the partial chambers and the partial ring-shaped channels. The side channel pump thereby has a high efficiency and particularly low radial dimensions. | 01-05-2012 |
| 20120014785 | STRUCTURE OF CIRCULATION FAN - A fan includes a casing that is composed of a front cover and a rear cover, a base mounted under the casing, and blades rotatably mounted in the casing. The base includes support frames symmetrically mounted thereto. The front and rear covers are each composed of a plurality of circular frames of different diameters. The rear cover has a lower portion that forms slots corresponding to the support frames so that the support frames are movably received through the slots respectively. A connection bar is connected to the rear cover so that the casing may undergo vertical and horizontal rotations through the arrangement of the slots for adjusting direction of airstream generated by the fan, thereby realizing an effect of indoor air circulation. Further, due to the arrangement of the rotation structure inside the casing, the outside appearance of the fan shows a sense of completeness of aesthetics. | 01-19-2012 |
| 20120045320 | AIR TURBINE STARTER TURBINE NOZZLE AIRFOIL - A vane profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Y-coordinates. | 02-23-2012 |
| 20120045321 | WIND TURBINE NACELLE - The present invention relates to a nacelle for a wind turbine, the nacelle having a first height in its installed position and a second height in its transported position, the first height being higher than the second height, comprising a bottom part having a bottom face and two opposite side faces defining a space and a width of the bottom part and a top part. In the transported position, the top part extends inside the width or outside the width in order to cover at least part of the space. The invention also relates to a transportation kit and a transport method. | 02-23-2012 |
| 20120076647 | METALLIC RADIUS BLOCK FOR COMPOSITE FLANGE - A disclosed fan containment case includes a fan case fabricated from a plurality of non-metallic composite layers with an attachment flange formed of both a composite portion and a metallic backing. The disclosed metallic backing is mounted on a rearward facing surface of a composite portion of the attachment flange. | 03-29-2012 |
| 20120087785 | MULTI-STAGE TURBOCHARGER ARRANGEMENT - The present invention relates to a multi-stage turbocharger arrangement ( | 04-12-2012 |
| 20120099975 | FAN CASE AND MOUNT RING SNAP FIT ASSEMBLY - A disclosed fan containment case includes a mount ring that supports a portion of the engine core. The mount ring includes openings and features that define a mounting location for the gas turbine engine. The example fan containment case includes a generally cylindrically shaped fan case that extends between an open front end and an open rear end. The mount ring is secured onto an outer surface of the fan case and includes a mounting lug and a plurality of openings for attachment of gas turbine engine components. | 04-26-2012 |
| 20120099976 | FAN CONTAINMENT SYSTEMS WITH IMPROVED IMPACT STRUCTURES - Methods and apparatus are provided for a fan containment system for a gas turbine engine having a plurality of fan blades includes a cylindrical casing with an inner surface surrounding the plurality of fan blades and an opposing outer surface; a first layer of fabric material positioned on the exterior surface of the cylindrical casing; and a shear thickening fluid impregnated within the first layer of fabric material. | 04-26-2012 |
| 20120107107 | ANTI-ROTATION SHROUD FOR TURBINE ENGINES - A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs. | 05-03-2012 |
| 20120107108 | RADIAL GAS EXPANDER - Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections ( | 05-03-2012 |
| 20120107109 | AIRCRAFT ENGINE NACELLE COMPRISING A MOBILE COWL MOVED BY ELECTRIC MOTORS - A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors. | 05-03-2012 |
| 20120114469 | COMPOSITE HUB FOR A PRESSURE WAVE SUPERCHARGER - The invention proposes that the shaft-hub connection of a rotatable cell rotor ( | 05-10-2012 |
| 20120121395 | METHOD FOR FABRICATING A GAS TURBINE ENGINE COMPONENT AND A GAS TURBINE ENGINE COMPONENT - A method for fabricating a gas turbine engine component including an inner ring, an outer ring and at least one strut connecting the inner ring with the outer ring includes the steps of connecting the inner ring to the outer ring via a load carrying edge of the strut, and attaching a side face component of the strut in abutment with the load carrying edge after the step of connecting the inner ring to the outer ring has been performed. A as turbine engine component fat by the method is also provided. | 05-17-2012 |
| 20120121396 | WIND ENERGY POWER ENHANCER SYSTEM - An enhanced multi-phased wind power generating system is disclosed that creates power from flow through an air inflow chamber and by second phase air flow that does not pass through the inflow chamber. In one embodiment, a turbine extends at least partially from the air inflow chamber whereby second phase air flow that may be directed, deflected or concentrated prevailing wind, may impinge the air blades to enhance the power generation of the system. In another embodiment, second phase air flow may be deflected by a configuration of air deflectors to create a low pressure over a flow tube to enhance power generation. Air deflectors and/or air scoops are described in any number of configurations to further increase and optimize power generation. In one embodiment an impingement chamber is attached to the inflow chamber and one or both chambers may comprise protective fencing material. | 05-17-2012 |
| 20120121397 | TURBINE ROTOR FOR A TURBOCHARGER, TURBOCHARGER AND METHOD FOR PRODUCING A TURBINE ROTOR - A turbine rotor for a turbocharger, in particular for a motor vehicle, has a turbine wheel which is formed in one piece and which has a turbine blade arrangement and a solid turbine wheel shoulder with a first end surface without cavities or depressions. A rotor shaft is formed in one piece and has a second end surface with a depression arranged coaxially with respect to the rotational axis. The first end surface of the turbine wheel shoulder is connected to a second end surface of the rotor shaft in a cohesive fashion by way of a friction weld. There is also provided a turbocharger and a method for producing a corresponding turbine rotor. | 05-17-2012 |
| 20120128474 | FLOW PATH FOR STEAM TURBINE OUTER CASING AND FLOW BARRIER APPARATUS - A steam turbine may include a turbine section including a rotor. An inner casing is provided about the turbine, the inner casing including an upstream end, a downstream end and an inner casing exhaust port positioned at the downstream end allowing exhaust steam to exit the inner casing. An outer casing is provided about the inner casing, the outer casing including an upstream end, a downstream end and an outer casing exhaust port positioned at the upstream end of the outer casing. A flow path extends between the inner casing and the outer casing through which the exhaust steam passes in an upstream direction from the inner casing exhaust port to the outer casing exhaust port. A flow barrier may be provided in the flow path between the inner casing and the outer casing. | 05-24-2012 |
| 20120128475 | Vortex Enhanced Wind Turbine Diffuser - A diffuser for a wind turbine where slots in said diffuser wall entrain air to enter into the diffuser with a swirl that is counter to the internal swirl created as a reaction to the turbine blades rotation as it extracts power such that the internal swirl and the externally introduced swirl cross over each other thereby causing vortices to form between them that energizes the internal flow and helps to prevent it from separating from the internal duct wall. Such a diffuser would beneficially consist of a radial array of repeated segments each comprising a radial portion of a duct with a wing emerging from behind said duct leading edge and spiraling out and backwards and connecting back onto the wing of the next segment round such that each segment's wing connects to the trailing neighboring segment wing just as the leading neighbors wing connects onto it, and that a gap is left between the spiral arms to permit external air to flow between the trailing edge of one segment wing and the leading edge of the adjacent wing. | 05-24-2012 |
| 20120134789 | Water Pump - A water pump includes a pump shaft surrounded by a pump housing having a tubular section. A pulley having a cylindrical section and a flange wall is mounted on an end section of the pump shaft. An impeller is mounted on the other end section of the pump shaft. A mechanical seal is coaxially disposed between the tubular section and the pump shaft. A bearing is coaxially disposed between the tubular section of the pump housing and the cylindrical section of the pulley. In this water pump, the pump shaft includes a coaxial small diameter shaft section located at its first part which is located axially between the mechanical seal and the flange wall. The small diameter shaft section has a diameter smaller than a diameter of a second part of the pump shaft on which the mechanical seal is disposed so as to form an annular step portion. | 05-31-2012 |
| 20120134790 | SYSTEM AND METHOD FOR STORING ENERGY - A system includes at least one body, a link for suspending the body for movement with gravity from a first elevation position to a second elevation position, and an electrical energy generator coupled with the body through the link to drive the generator to generate electricity upon movement of the body with gravity from the first to the second elevation position. The at least one body has a mass of at least approximately 100 tonnes; the first and the second elevation positions define a distance therebetween of at least approximately 200 meters; and/or the system further includes an operator configured to operate the link to controllably move the at least one body against gravity from the second to the first elevation position to increase a gravitational potential energy of the at least one body, and to maintain the gravitational potential energy of the at least one body. | 05-31-2012 |
| 20120141258 | AIR TURBINE STARTER - An air turbine starter is provided and includes a rotor including turbine blades, which is rotatable about a rotational axis, a housing including a portion thereof radially surrounding the turbine blades to define a pathway along which fluids flow to interact with the turbine blades and a containment ring affixed to an exterior of the portion of the housing radially surrounding the turbine blades. | 06-07-2012 |
| 20120141259 | BLADE SEGMENT AND FLUID FLOW MACHINE - A blade segment ( | 06-07-2012 |
| 20120156017 | SHAFT SUPPORT FOR AIR CYCLE MACHINE - An example shaft support includes a cylindrical body establishing a bore extending along an axis. The bore is configured to receive a shaft. Openings are provided in the cylindrical body and distributed circumferentially about the axis. The openings are positioned radially outward of the bore. Each of the openings has a cross-sectional area. The ratio of a total cross sectional area of the openings to a diameter of the cylindrical body is between 0.0963 and 0.0964. | 06-21-2012 |
| 20120156018 | TURBINE SHROUD FOR AIR CYCLE MACHINE - A turbine shroud for an air cycle machine includes a wall inner surface which at least partially defines a turbine flowpath, the wall inner surface defined by set of points in Table T-1 scaled by a desired factor. | 06-21-2012 |
| 20120156019 | FAN MODULE - An exemplary embodiment of a fan module includes fan units, and each fan unit includes a box-shaped shell, a guiding plate, and a torsion spring. The box-shaped shell includes a bottom plate and two opposite side walls substantially perpendicular to the bottom plate, and each side wall has a vent defined therein. The guiding plate is rotatable relative to the bottom plate of the shell. The torsion spring includes a first torsion arm, a second torsion arm, and a coil portion. The first torsion arm and the second torsion arm are urged against the bottom plate and the guiding plate respectively by torque force applied from the coil portion. Thereby, the guiding plate is driven to a position adjacent and generally parallel to one of the side walls to obstruct the corresponding vent by the second torsion arm. | 06-21-2012 |
| 20120163961 | FLEXIBLE HOUSING FOR STEAM TURBINE EXHAUST HOOD - A flexible housing is arranged along an axial centerline of a rotor shaft of a steam turbine. The flexible housing extends between an exhaust hood endcover and a seal end packing housing on a separate supporting standard. The flexible housing includes a top cover portion and a bottom cover portion with a flanged horizontal joint that permits removal and replacement without need to remove the exhaust hood cover and the rotor shaft. The flexible housing encloses the rotor shaft with a first cylindrical element and a second cylindrical element of a different radius joined with an thin member that flexes to absorb expansion and contraction of the turbine exhaust hood. | 06-28-2012 |
| 20120163962 | TURBOMACHINE ELECTRIC CONNECTION AND METHOD - A turbomachine includes an expander; a central region having a first end attached to the expander; a compressor attached to a second end of the central region; an electrical device provided inside the central region; and an electrical connection including a first part and a second part, the first part being configured to be removably attached directly to the second part. The first part is configured to be removably attached to an external surface of an external casing of the central region, and the second part is configured to be fixedly attached to a bundle. | 06-28-2012 |
| 20120163963 | STRUCTURE FOR GAS TURBINE CASING - A structure for a gas turbine casing, capable of preventing gas from leaking when the structure is subjected to pressure. A structure for a gas turbine casing, divided by a horizontal plane at flange sections into two halves comprising an upper-half casing ( | 06-28-2012 |
| 20120183392 | CAST TURBINE HOUSING WITH STAMPED VOLUTE - A turbine housing includes a housing having a volute section. A volute insert is positioned within an interior portion of the volute section. The surface of the volute insert may be smoother than the interior surface of the volute to reduce turbulence and increase air flow within the volute. | 07-19-2012 |
| 20120189437 | HERMETIC COMPRESSOR - The present invention refers to a hermetic compressor and, more specifically, a hermetic compressor comprising a centrifugal pump ( | 07-26-2012 |
| 20120195744 | ENGINE HOT SECTION COMPONENT AND METHOD FOR MAKING THE SAME - One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 08-02-2012 |
| 20120213630 | HIGH-PERFORMANCE TURBINE WITH INCREASED SPECIFIC POWER - A high-performance turbine, particularly with increased specific power, including a rotor and a distribution apparatus which is adapted to convey a fluid stream onto the elements of the rotor for the rotation of the rotor about its own rotation axis, where the rotor includes a plurality of thrust ducts adapted to receive the fluid stream conveyed by the distribution apparatus to generate a rotary thrust on the surrounding walls of the thrust ducts, the turbine further including at least one slot, which is formed on the walls of the thrust ducts and/or of the distribution apparatus and is adapted to connect the fluid stream to the outside environment of the turbine, where at least one of the thrust ducts and the distribution apparatus crossed by the fluid stream includes at least one portion that converges in the direction in which the fluid stream travels, which is defined upstream of the slot in the direction of travel of the fluid stream for the at least local lowering of the pressure inside the thrust ducts and/or the distribution apparatus, which are crossed by the fluid stream, below the value of the pressure of the filling fluid of the outside environment, with consequent suction of the filling fluid into the thrust ducts and/or the distribution apparatus which are crossed by the fluid stream. | 08-23-2012 |
| 20120219406 | PIPELINE PUMP SHAPED BY STAMPING AND WELDING - A pipeline pump shaped by stamping and welding, comprises a pump body, a pedestal, a pump rear cover and a motor installed at the opening of the pump body, and an impeller arranged inside the pump body. The pump body is comprised of an inner cylinder and an outer cylinder. A flow guide part, the impeller, an exhaust part, and the pump rear cover mounted on the opening of the outer cylinder are coaxially arranged upwards in turn from the opening of the inner cylinder. The impeller is axial suction and radial discharge. The disk bottom of the flow guide part is sealed with the opening of the inner cylinder. The impeller is coaxially arranged inside the flow guide part, and a flow guide vanes corresponding to a radial exhaust port of the impeller are provided on a circumferential wall of the flow guide part. | 08-30-2012 |
| 20120219407 | VACUUM PUMP - Vacuum pump for pumping gas from a process chamber, the pump comprising: a rotor supported for rotation in a pumping chamber by a drive shaft, the shaft extending through a shaft bore in a wall of the pumping chamber extending transversely to the drive shaft, and a seal arrangement provided between the shaft and the transverse wall for resisting the passage of gas through the shaft bore, wherein on rotation of the rotor gas is pumped from a low pressure region at an inlet of the pumping chamber to a high pressure region at an outlet of the pumping chamber, and wherein the rotor and the transverse wall are spaced apart by an axial clearance along which back leakage of gas can flow from the high pressure region to the low pressure region, and an additional leakage path for back leakage is formed spaced away from the seal arrangement along which gas can flow without contact with the seal arrangement so that the amount of gas which contacts the seal arrangement during use of the pump is reduced. | 08-30-2012 |
| 20120219408 | CYLINDRICAL STRUCTURE AND METHOD FOR MANUFACTURING THE SAME - A method for manufacturing a cylindrical structure having an axial direction includes: winding a fabric around a mandrel in a circumferential direction that is perpendicular to the axial direction, the fabric containing first fibers oriented in a first direction intersecting the circumferential direction; winding a roving into a helical shape around the mandrel, the roving containing second fibers oriented in a longitudinal direction of the roving; and joining the fabric and the roving together by using a resin. | 08-30-2012 |
| 20120237343 | TURBOCHARGER - A variable geometry turbocharger includes a bearing housing rotatably supporting a turbine impeller; and an exhaust nozzle changing the flow rate of an exhaust gas supplied to the turbine impeller, wherein the exhaust nozzle has an exhaust inlet wall disposed at the bearing housing side, the turbocharger has a seal member exhibiting a ring shape and sealing a gap formed between the bearing housing and the exhaust inlet wall, and an inner circumferential edge of the seal member firmly contacts the bearing housing and an outer circumferential edge of the seal member firmly contacts the exhaust inlet wall. | 09-20-2012 |
| 20120243980 | Rotatable Dry Air Supply - A rotatable dry air supply system for a wind turbine is provided. The system includes a rotatable dry air supply housing connected to a rotatable hub having a plurality of wind turbine blades connected thereto. The housing is rotatable with the hub and includes a compressor and a moisture trap for removing moisture from the compressed air. The moisture trap may include a plurality of outlet ports arranged around a casing of the moisture trap. The moisture purged from the outlet ports may exit through a moisture outlet in the housing of the rotatable air supply. In some arrangements, the outlet may be heated. | 09-27-2012 |
| 20120251305 | IMPACTOR CONTAINMENT - A containment system | 10-04-2012 |
| 20120251306 | Fan Rotor Support - A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft. | 10-04-2012 |
| 20120257963 | INNER DIAMETER SHROUD ASSEMBLY FOR VARIABLE INLET GUIDE VANE STRUCTURE IN A GAS TURBINE ENGINE - An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment. | 10-11-2012 |
| 20120263582 | Ceramic matrix composite shroud attachment system - Shroud assembly for use in a turbine, having an outer shroud having a side proximate to flow of operative fluid of the turbine, the side having a boss and an outer shroud aperture extending through the boss. An inner shroud is located between the side of the outer shroud proximate to the flow of operative fluid and the operative fluid flow of the turbine, the inner shroud having an inner shroud aperture which is dimensioned to fit over the boss. | 10-18-2012 |
| 20120263583 | FAN CASING FOR A TURBOFAN ENGINE - A fan casing for a turbofan engine including an annular casing component of composite material including a body portion having an outwardly directed stiffening flange at one end, the stiffening flange being connected to the body portion by a radially outwardly stepped region, the fan casing also including a metallic ring which is coaxial with the annular casing component, the metallic ring being situated at least partially within the stepped region and being secured to the annular casing component. | 10-18-2012 |
| 20120269618 | BLADE SUPPORT IN A QUASITURBINE PUMP - A pump comprises a housing having an inner contour and defining an ovaloidal chamber with a rhomboidal rotor assembly positioned therein and being configured to rotate. The housing includes intake and exhaust ports in communication with the chamber providing for intake of fluid therein and exhaust of fluid therefrom. A movement imparting assembly imparts a rotational movement to the rhomboidal rotor assembly. The rhomboidal rotor assembly comprises four blades, adjoined at four joints comprising rotatable members spaced interposed between two adjacent blades and being spaced therefrom. The pump can be a compressor or and engines and can be used in a variety of fields. | 10-25-2012 |
| 20120269619 | FLUID-FLOW MACHINE - A fluid-flow machine includes at least one rotor having a rotary element with a plurality of rotor blades arranged on the rotary element, and a circumferential casing having a central axis and surrounding the rotor. The circumferential casing or a part connected thereto has an annular space surface on the inside, which delimits a flow duct of the fluid-flow machine radially outwards. The annular space surface has a structuring at least in one area adjoining a rotor on the circumferential side. At least one structuring of the annular space surface has, relative to the central axis of the circumferential casing, a circumferentially asymmetrical design. | 10-25-2012 |
| 20120275909 | MICRO COOLING FAN - A micro cooling fan comprises a housing and a main circuit board. The housing has an accommodation space, a first inner surface, and a gap. The gap is in communication with the accommodation space, and two opposite side edges of the gap have a groove respectively. The main circuit board comprises a first circuit board and a second circuit board. The first circuit board has a stator, the second circuit board has a driving circuit, and the stator is electrically connected to the driving circuit. The first circuit board is disposed on the first inner surface, and the second circuit board is embedded into the grooves and blocks the gap. | 11-01-2012 |
| 20120282083 | TURBINE CASING HAVING LEDGE RING PARTITION APERTURE - A turbine casing segment is disclosed. In one embodiment, a turbine casing segment is disclosed including: a plurality of stage segments; a plurality of ledge ring partitions separating the plurality of stage segments, wherein at least one of the plurality of ledge ring partitions has an axially extending aperture therethrough; and a substantially rounded extraction aperture located flush with an inner surface of one of the plurality of stage segments. | 11-08-2012 |
| 20120282084 | RECEPTACLE DEVICE FOR THE ROTOR ASSEMBLY OF A TURBOCHARGER - A turbocharger has a turbocharger housing with at least one section that is divided in the longitudinal direction into at least two housing halves. A receiving device for receiving a rotor assembly of the turbocharger can be fastened to at least one half of the housing. | 11-08-2012 |
| 20120288363 | CEILING-MOUNTED INDOOR UNIT FOR AIR CONDITIONING APPARATUS - A ceiling-mounted indoor unit for an air conditioning apparatus is disposed in a ceiling of an air-conditioned room. The ceiling-mounted indoor unit includes a casing having an air outlet formed along a peripheral edge portion of an undersurface of the casing, at least four horizontal blades rotatably disposed in the air outlet, and a controller. The horizontal blades have airflow-direction angles that are independently changeable in an up-and-down direction. The control unit controls the horizontal blades such that at least two first horizontal blades of the at least four horizontal blades synchronously swing while taking the same posture. The first horizontal blades are adjacent to each other, and a combination of the at least four horizontal blades forming the first horizontal blades shifts in order along the peripheral edge portion. | 11-15-2012 |
| 20120294708 | Apparatus to protect a radon fan from mechanical failure due to damage from falling objects from within the radon mitigation system - This apparatus protects a radon fan from damage due to falling water, ice, critters and debris and is installed above the radon fan and protects the fan in several ways. | 11-22-2012 |
| 20120301281 | FAN MODULE - A fan module suitable for an electronic apparatus is provided. The fan module includes a bottom plate, a top cover. a sidewall, a heat-dissipating fan and a housing. The sidewall is assembled between the top cover and the bottom plate. The sidewall, the top cover and the bottom plate together form an accommodating space. The heat-dissipating fan is disposed on the bottom plate and located in the accommodating space. The housing is stacked on the top cover. | 11-29-2012 |
| 20120301282 | WIND-COLLECTING TOWER FOR A WIND POWER GENERATOR - The present invention relates to a wind-collecting tower for a wind power generator, including a cylindrical wind tunnel which stands upright on a base, and which has a circumferential surface with wind inlet ports for introduction of wind; a guide unit having guide passages arranged on the circumference of the wind tunnel to guide wind introduced from the outside to the wind inlet ports; louvered windows formed on the guide passages of the guide unit and spaced apart from the wind tunnel, such that the wind introduced into the guide unit is guided downwardly by the guide unit and introduced into the wind inlet ports of the wind tunnel; and one or more support frames which are arranged transversely on the respective guide passages, and which have one or more through-holes covered by the louvered windows. | 11-29-2012 |
| 20120301283 | TURBINE WITH UNEVENLY LOADED ROTOR BLADES - An unevenly loaded turbine rotor blade is disclosed herein, the blade including a power-extracting region adapted for radially-varied (relative to the axis of rotation) power extraction per mass flow rate. The pitch and/or shape of the airfoil at a first radial position may be configured, so that power extraction per mass flow rate at the first radial position is different than power extraction per mass flow rate at a second radial position. Thus, the power-extracting region may be advantageously configured to take advantage of a non-uniform flow profile across a rotor plane such as may be induced using a shrouded turbine. | 11-29-2012 |
| 20120308369 | LAMINATE THERMAL INSULATION BLANKET FOR AIRCRAFT APPLICATIONS AND PROCESS THEREFOR - A thermal insulation blanket for an aircraft engine, and processes for producing the thermal insulation blanket to have low thermal conductivity and high temperature capability. The thermal insulation blanket has a layered construction that includes an aerogel insulation material, a composite layer disposed at a first surface of the aerogel insulation material, and a backing layer disposed at an opposite surface of the aerogel insulation material so that the aerogel insulation material is encapsulated between the composite and backing layers. The composite layer contains a resin matrix material reinforced with a fiber reinforcement material. | 12-06-2012 |
| 20120315132 | THIN VENTILATED SEAT FOR A VEHICLE AND ITEMS OF FURNITURE - An air conditioning unit includes a shaped body forming at least one part of a seat cushion. The shaped body has a seating surface and an opposite lower side. An air flow module is arranged at the lower side of the shaped body. The air flow module includes an air mover and has an air inlet opening and an air outlet opening. The shaped body has at least one air through-hole extending from the seating surface to the air flow module. The air flow module is in fluid communication with the at least one air through-hole in the shaped body. At least one channel extends in a radial direction adjacent the lower surface of the shaped body. The air flow module is in fluid communication with the at least one channel, and provides airflow between the seating surface of the shaped body and the at least one channel. | 12-13-2012 |
| 20120328421 | METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE - A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion. | 12-27-2012 |
| 20120328422 | EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger ( | 12-27-2012 |
| 20120328423 | GAS TURBINE AND REPAIRING METHOD OF GAS TURBINE - A gas turbine includes ring segments and isolation rings that surround a channel for high-temperature gas W from an outer peripheral side, blade rings formed in an annular shape on the outer peripheral side of the ring segments and the isolation rings, and supporting members fitted into fitting concave portions recessed from the end faces of the blade rings in the direction of the axis and supporting the ring segments and the isolation rings. An inner wall surface of the fitting concave portion has a first inclined surface that inclines so as to narrow gradually from an opening edge of the fitting concave portion toward the inside of the blade ring in the direction of the axis, and the supporting member has a second inclined surface that inclines so as to correspond to the first inclined surface. | 12-27-2012 |
| 20120328424 | INTAKE CONDUIT ELEMENT AND COMPRESSOR ARRANGEMENT THEREFROM - Intake manifold element ( | 12-27-2012 |
| 20130004303 | FAN ASSEMBLY - A fan assembly includes a case, a bracket and a fan module. The cage includes a ventilation plate. An installation portion and a positioning post are located on the ventilation plate. The fan module is secured to the ventilation plate and includes a bracket and a fan secured to the bracket. The bracket includes a body, a first sidewall, and a second sidewall. The first and second sidewalls are located on opposite sides of the body. The first sidewall defines a first receiving slot and a first positioning hole. The second sidewall defines a second receiving slot and a second positioning hole. The first positioning hole is aligned with the second positioning hole. An area of the first receiving slot is larger than that of the second receiving slot. The positioning post is engaged in the positioning hole. The installation portion is received in the first receiving slot. | 01-03-2013 |
| 20130004304 | FAN - A fan includes a motor including a rotating portion and a stationary portion; an impeller including a plurality of blades and a blade support portion to which the blades are fixed, and arranged to cover the motor; and a housing including a lower plate portion arranged on a lower side of the blades, a side wall portion arranged to cover sides of the blades, and an upper plate portion arranged on an upper side of the blades and including an air inlet arranged to extend through the upper plate portion in an axial direction. A lower surface of the blade support portion includes a balance correction portion arranged to extend in a circumferential direction. The lower plate portion includes a through hole arranged to overlap with the balance correction portion in the axial direction to make a portion of the balance correction portion viewable from below the lower plate portion. | 01-03-2013 |
| 20130017073 | WALL RING FOR AXIAL FANAANM Sauer; ThomasAACI IdsteinAACO DEAAGP Sauer; Thomas Idstein DEAANM Best; DieterAACI IngelfingenAACO DEAAGP Best; Dieter Ingelfingen DEAANM Beck; SvenAACI KrautheimAACO DEAAGP Beck; Sven Krautheim DEAANM Weiss; ChristianAACI Mulfingen-ZaisenhausenAACO DEAAGP Weiss; Christian Mulfingen-Zaisenhausen DE - The invention relates to a wall ring for an axial fan comprised of a supporting frame ( | 01-17-2013 |
| 20130017074 | Rotor Fastening Arrangement - A rotor fastening arrangement, particularly for connecting a drive shaft and a rotor hub of a centrifugal pump assembly, having a fitting surface and at least one contact surface at the drive-shaft end. Respective ends of the drive-shaft ( | 01-17-2013 |
| 20130028717 | FLAP SEAL AND SEALING APPARATUS - A sealing plate for sealing a gap between two primary sealing plates is provided. The sealing plate has a sealing portion and a connector portion, wherein the sealing portion has a width which is greater than a width of the connector portion. An apparatus for sealing a gap between two structural components of a turbine, the apparatus including a plurality of primary sealing components, and at least one sealing plate is also provided, as is a turbine having a plurality of structural components with a gap between said structural components, wherein the gap is sealed by a plurality of sealing components, the sealing components comprising a plurality of primary sealing components and at least one sealing plate. | 01-31-2013 |
| 20130028718 | STRUT, A GAS TURBINE ENGINE FRAME COMPRISING THE STRUT AND A GAS TURBINE ENGINE COMPRISING THE FRAME - A strut is provided for being arranged between an annular inner structural casing and an annular outer structural casing in a gas turbine engine frame for carrying loads between the inner and outer structural casing during operation. The strut includes a first tube, which is configured to house a service line or pipe between the inner and outer structural casing. The strut includes a second tube, which is configured to house a fastening element for rigidly connecting the inner and outer structural casing. The first and second tube are arranged in a side-by-side relationship and rigidly attached to each other. | 01-31-2013 |
| 20130034430 | PORTABLE SWIM CURRENT GENERATOR - A swim current generator apparatus includes an enclosure and a motor shroud, the motor shroud enclosing a motor coupled to a propeller and having openings therein to permit the intake and discharge of water by the propeller, wherein the motor shroud is moveable between a retracted position within the enclosure and an extended position outside the enclosure. | 02-07-2013 |
| 20130034431 | CAMBERED AERO-ENGINE INLET - A propulsion system includes an engine with a fan and a nacelle that circumscribes the engine. The engine defines an axis. A distance between a forwardmost point at the top of the nacelle and at the front of the nacelle to a forwardmost point of the fan is greater than a distance between a forwardmost point at the bottom of the nacelle and at the front of the nacelle. | 02-07-2013 |
| 20130034432 | CORRUGATED CORE COWL FOR A GAS TURBINE ENGINE - A core nacelle for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a core cowl positioned adjacent to an inner duct boundary of a fan bypass passage having an associated cross-sectional area that radially extends between a fan exhaust nozzle and the inner duct boundary. The core cowl includes at least one groove that is selectively exposed to change the cross-sectional area at an axial location of the fan exhaust nozzle. | 02-07-2013 |
| 20130045092 | AXIAL FLOW FAN - A fan includes an impeller having a plurality of blades. Each of the plurality of blades has a trailing edge portion positioned rearmost in a rotation direction and a leading edge portion positioned foremost in the rotation direction. A curved line interconnects the trailing edge portion and the leading edge portion at the shortest distance on an imaginary cylindrical surface. Each of the blades includes a lower surface facing downward in the direction of the center axis and an upper surface facing upward in the direction of the center axis. In the fan, L | 02-21-2013 |
| 20130045093 | METHOD FOR THE MANUFACTURE OF A COMPONENT FOR HIGH THERMAL LOADS, A COMPONENT PRODUCIBLE BY THIS METHOD AND AN AIRCRAFT ENGINE PROVIDED WITH THE COMPONENT - A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient α | 02-21-2013 |
| 20130058770 | FASTENING FLANGE - A flange for fastening a line to a pump casing, includes: a pump casing passage; and a plurality of stop members protruding in the passage and angularly distributed around the passage, the position of the flange being angularly adjustable by the stop members. A pump may include the fastening flange. A method for adjusting the position of the flange in relation to the pump is also disclosed. This method makes it possible to avoid the position of the pump casing being imposed by the orientation of the fastening flange of the pump casing. | 03-07-2013 |
| 20130064649 | PIPING ASSEMBLY AND METHOD FOR CONNECTING INNER AND OUTER SHELL IN TURBINE SYSTEM - A piping assembly and a method for connecting an inner shell and an outer shell in a turbine system are disclosed. The piping assembly includes an inner fitting for connection to the inner shell and an outer fitting for connection to the outer shell. The piping assembly further includes an attenuation member extending between the inner fitting and the outer fitting and comprising an attenuation curve. The attenuation curve permits movement of the attenuation member in at least one of a longitudinal direction, a radial direction, or a tangential direction. | 03-14-2013 |
| 20130064650 | FAN UNIT ASSEMBLY - A fan unit assembly includes a fan rack, fan units and handles. The fan rack includes a carrier and parallel partition boards erected on the carrier to define fan-disposing regions. The partition board has at least one first positioning part and at least one first guiding part facing the corresponding fan-disposing region. The fan unit has two side surfaces and a front surface. The front surface connects the side surfaces. The side surfaces respectively have a second guiding part engaged with the first guiding part. The fan unit is suitable to move along the first guiding part through the second guiding part. The handles are disposed at the front surface and both ends thereof are bent to form two pivot portions respectively pivoted on the side surfaces. Each pivot portion has a second positioning part. When the handle rotates towards the front surface, the positioning parts interfere with each other. | 03-14-2013 |
| 20130064651 | TURBINE CASING AND METHOD OF MANUFACTURING THEREOF - A design for a casing of a large turbine is described with the casing including at least a front section, a middle section and an end section designed such that changes to the mold of the casing required to provide for a change in rotational speed to adapt the turbine to a different power grid frequency are limited to the mold for the middle section of the casing. | 03-14-2013 |
| 20130064652 | PROPELLER NOZZLE - A propeller nozzle for watercraft, includes a nozzle and a propeller having at least one propeller blade which can rotate about a propeller axis and which spans a propeller area through rotation about the propeller axis. The propeller blade has a propeller blade end region wherein the propeller is disposed inside the nozzle in such a manner that a circumferential gap in the circumferential direction of the propeller nozzle is formed between the propeller end region and the inner wall of the nozzle. A marginal flow running from a nozzle in the area of the inner wall of the nozzle can flow through the gap, wherein the performance losses which occur due to turbulence of the marginal flow during flow around the propeller blade end region are kept as low as possible. Flow guiding apparatus guides at least one part of the marginal flow onto the propeller area. | 03-14-2013 |
| 20130064653 | METHOD FOR MANUFACTURING AIRCRAFT ENGINE CASES WITH BOSSES - A method of manufacturing turbine engine casings having at least one boss includes, in one exemplary embodiment, forming an engine casing having an outer wall, machining a tapered opening through the casing outer wall, and machining a tapered portion in a metal plug where the tapered portion is sized to mate with the tapered opening in the casing outer wall. The method also includes inserting the metal plug into the tapered opening in the casing outer wall, and welding the metal plug to the casing. | 03-14-2013 |
| 20130064654 | HOUSING FOR A HIGH EFFICIENCY WIND TURBINE - A housing for a wind turbine includes a plurality of spine members with a central rib and opposed channels. Frame members are attached to adjacent spine members. The housing includes divergent frame members having a pair of longitudinal members which are inserted into channels of a spine member. The housing includes central support members, each central support member is attached to a divergent frame member. Each of the central support members is attached near the center of one of the divergent frame members. The housing also includes outer plates, each outer plate attached to and between adjacent spine members. Channels face in the opposite direction from adjacent channels on the spines. An inner shroud is attached to the spine members. Air passages are created underneath the arcuate outer plates. A cowling is attached to the end plates. | 03-14-2013 |
| 20130064655 | EXHAUST GAS TURBOCHARGER HOUSING - A turbine housing of an exhaust gas turbocharger, includes an outer housing in which an inner housing with a tubular nozzle and an outlet duct for connection to an exhaust gas system is arranged. The outlet duct is coupled with the tubular nozzle for movement relative to the nozzle via a seal ring. The seal ring is inwardly everted and pushed onto the nozzle and embraced by an inner-housing support ring, so that a fluid tight fit on the inner housing nozzle is ensured. The seal ring is further pushed onto the outlet duct and there also coupled onto the outlet duct with an outlet duct support ring in a fluid tight manner so that an especially durable connection is created. Both support rings are additionally coupled in a materially bonded manner with the seal ring and the outlet duct nozzle or with the inner housing. | 03-14-2013 |
| 20130064656 | TURBINE HOUSING OF AN EXHAUST GAS TURBOCHARGER - A turbine housing of an exhaust gas turbocharger includes an outer housing, in which an inner housing with a tubular nozzle and an outlet duct for connection to an exhaust gas system is arranged, wherein the outlet duct is coupled to the tubular nozzle via a sealing lip for relative movement. The sealing lip is inwardly evertedly pushed onto the nozzle and for positional fixing, a sliding sleeve is further arranged on the nozzle, wherein the sliding sleeve and the nozzle form a gap in which an end of the sealing lip is received. This avoids that the sealing lip lifts of due to pressure differences and thus that gas leaks occur. Further, an end of the sealing lip is arranged so as to be thermally protected. | 03-14-2013 |
| 20130064657 | INTERMEDIATE HOUSING OF A GAS TURBINE HAVING AN OUTER BOUNDING WALL HAVING A CONTOUR THAT CHANGES IN THE CIRCUMFERENTIAL DIRECTION UPSTREAM OF A SUPPORTING RIB TO REDUCE SECONDARY FLOW LOSSES - Intermediate housing ( | 03-14-2013 |
| 20130071237 | HOUSING FOR AIR MACHINE HAVING DRAIN HOLES - A housing for use in an air machine includes a housing body for housing at least one rotor. The housing body has at least one conduit for connection to a connecting conduit. The conduit has a drain hole adjacent an end of the conduit. The drain hole is formed at an angle relative to a plane made perpendicular to a center axis of said conduit. An air machine, an air machine assembly and a method are also disclosed. | 03-21-2013 |
| 20130078086 | TURBO MACHINE WITH A DEVICE FOR PREVENTING A SEGMENT OF NOZZLE GUIDE VANES ASSEMBLY FROM ROTATING IN A CASING; ROTATION-PROOFING PEG - A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation. | 03-28-2013 |
| 20130084171 | TURBINE DRUM ROTOR RETROFIT - Systems for increasing the efficiency of a turbine and an overall power plant system are disclosed. In one embodiment, a turbine includes: an outer shell including a set of grooves configured to complement components of a wheel and diaphragm steam path section; a drum rotor disposed within the outer shell; a set of shell converts connected to the outer shell via the set of grooves, the set of shell converts configured to complement components of the drum rotor; and a working fluid passage substantially defined by the drum rotor and the set of shell converts. | 04-04-2013 |
| 20130084172 | TURBINE EXHAUST SECTION STRUCTURES WITH INTERNAL FLOW PASSAGES - A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, an inner cavity disposed between the inner exhaust wall and an inner casing, and a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the inner cavity to the outer cavity. | 04-04-2013 |
| 20130089414 | STRIP SEALS - A strip seal for providing a seal between adjacent components, which include a first groove and a second groove angled with respect to and intersecting the first groove. The grooves of respective components are opposed to one another when the components are assembled. The strip seal includes a first strip section to span between and be received in the opposed first grooves, and a second strip section to span between and be received in the opposed second grooves. One end of the first strip section is arranged to butt against the second strip section at the intersection of the grooves. The other end of the first strip section has at least one deformable projection that can engage the end of the first groove. The projection deforms as it engages the end of the groove and urges the end of the first strip section against the second strip section. | 04-11-2013 |
| 20130094948 | INTAKE CHARGED PUMP FOR DELIVERING A LIQUID - An intake charged pump for pumping liquid and which has an intake duct that extends to the suction area of the pump. The pump has a duct through which a jet stream flows to the suction area. A nozzle arrangement in the intake duct accelerates the liquid which is returned via the jet stream and supports the suction of a suction stream of the liquid from a storage container. A nozzle of the nozzle arrangement leads into the mixing chamber at an acute angle in a such way that the jet stream, leaving the nozzle, creates a common mixing stream with the suction stream from the storage container, and through which partial streams having essentially the same pressure and energy content, can be delivered to the front and back suction pockets of the double chamber pump. | 04-18-2013 |
| 20130101403 | AERODYNAMIC MODIFICATION OF A RING FOIL FOR A FLUID TURBINE - A ring fluid foil including a modified trailing portion for a shrouded fluid turbine and shrouded fluid turbine including such ring fluid foils are described herein. The modification of the trailing portion increases flow turning by the fluid foil without, or with reduced, boundary layer separation on a suction side of the fluid foil. | 04-25-2013 |
| 20130101404 | ENCLOSURE AND MANIFOLD FOR ADAPTING NONCONFORMING FANS FOR USE IN HARSH OR WET ENVIRONMENTS - A fan enclosure that has manifolds connected to the inlet and outlet of the fan that provides an airtight connection. The manifolds, once connected to the enclosure, provide a pass through of the enclosure for the fan, thereby not requiring the enclosure to be pressurized. A condensate bypass can be installed both on the discharge manifold and the fan impeller body. Both condensate bypasses can be piped to the inlet manifold, preventing moisture accumulation in the fan and the enclosure. The fan enclosure helps prevent contamination and explosive gas in the air stream from coming in contact with the fan motor's electrical components and bearings. The fan enclosure reduces the contamination of the impeller bearing, does not draw or push air through the electrical conduit connected to the enclosure, and the enclosure is not required to be airtight to preform properly. | 04-25-2013 |
| 20130108420 | LAYERED SPLINE SEAL ASSEMBLY FOR GAS TURBINES | 05-02-2013 |
| 20130108421 | ABRADABLE CERAMIC COATINGS AND COATING SYSTEMS | 05-02-2013 |
| 20130108422 | COMPOSITE MATERIAL TURBOMACHINE ENGINE BLADE OR VANE, COMPRESSOR STATOR SEGMENT OR TURBINE NOZZLE SEGMENT INCORPORATING SUCH VANES AND METHOD FOR MANUFACTURING SAME | 05-02-2013 |
| 20130108423 | AIR-BLOW WORKING MACHINE | 05-02-2013 |
| 20130115065 | ASYMMETRIC RADIAL SPLINE SEAL FOR A GAS TURBINE ENGINE - A shroud apparatus for a gas turbine engine includes: an annular shroud segment having an arcuate bottom wall defining an arcuate inner flowpath surface, spaced-apart forward and aft walls extending radially outward from the bottom wall, and spaced-apart side walls extending radially outward from the bottom wall and between the forward and aft walls, each side wall defining an end face which includes: an axial slot extending in a generally axial direction along the end face; a first radial slot extending in a generally radial direction along the end face, and intersecting the axial slot; an axial spline seal received in the axial slot; and a first radial spline seal having an L-shape with radial and axial legs, the radial leg being substantially longer than the axial leg, wherein the radial leg is received in the first radial slot, and the axial leg is received in the axial slot. | 05-09-2013 |
| 20130115066 | CENTRIFUGAL FAN - A centrifugal fan comprises an impeller and a casing. The impeller includes a hub and a plurality of blades. The casing comprises an upper casing, a lower casing, at least one protrusion, a first inlet opening and a second inlet opening. The lower casing is disposed opposite to the upper casing and connected to the upper casing to form an accommodation room for receiving the impeller. The protrusion is formed on the upper casing and/or the lower casing inside the casing and immediately surrounds the blades. The first inlet opening is defined on the upper casing and comprises a primary inlet opening augmented by a secondary inlet opening. The second inlet opening is defined on the lower casing. The protrusion surrounds the first inlet opening and/or second inlet opening. | 05-09-2013 |
| 20130121813 | FLEXIBLE SEAL SYSTEM FOR A GAS TURBINE ENGINE - A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket. | 05-16-2013 |
| 20130121814 | TURBOJET ENGINE NACELLE - A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. | 05-16-2013 |
| 20130129490 | FAN ASSEMBLY - A nozzle for a fan assembly has an air inlet, an annular air outlet, and an interior passage for conveying air from the air inlet to the air outlet. The interior passage is located between an annular inner wall, and an outer wall extending about the inner wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The inner wall is eccentric with respect to the outer wall so that the cross-sectional area of the interior passage varies about the bore. The variation in the cross-sectional area of the interior passage can control the direction in which air is emitted from around the air outlet to reduce turbulence in the air flow generated by the fan assembly. | 05-23-2013 |
| 20130129491 | WATER DRAINAGE SYSTEM FOR BLOWER - A water drainage system for a blower, including a shell body ( | 05-23-2013 |
| 20130129492 | TURBOCHARGER - A turbocharger ( | 05-23-2013 |
| 20130142633 | TURBOMACHINE COMPONENT MACHINING METHOD - An exemplary component manufacturing method includes scanning a first surface of a component to determine a location of pocket surfaces of the first surface. The method machines apertures in the component from a second, opposite surface of the component. The apertures each have a cooling air inlet within one of the pocket surfaces and a cooling air outlet within the first surface. | 06-06-2013 |
| 20130142634 | METHOD FOR MOUNTNG SHIELDING ON A TURBINE CASING, AND MOUNTING ASSEMBLY FOR IMPLEMENTING SAME - A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads. | 06-06-2013 |
| 20130156555 | BRAZE MATERIALS, BRAZING PROCESSES, AND COMPONENTS WITH WEAR-RESISTANT COATINGS FORMED THEREBY - Braze materials, brazing processes, and coatings produced therefrom, for example, a wear-resistant coating suitable for protecting surfaces subjected to wear at high temperatures. The braze material includes first particles formed of a metallic alloy and second particles formed of a cobalt-base braze alloy having a melting point below the melting point of the first particles. The braze alloy consists of, by weight, 3.5 to 15.0% silicon, 2.0 to 6.0% boron, and the balance cobalt and incidental impurities, and the second particles constitute at least 30 up to 90 weight percent of the first and second particles combined. Following a brazing cycle performed on the braze material, a wear-resistant coating is formed in which the first particles are dispersed in a matrix of the braze alloy. | 06-20-2013 |
| 20130156556 | LOW-DUCTILITY TURBINE SHROUD - A shroud segment for a gas turbine engine, the shroud segment constructed from a composite material including reinforcing fibers embedded in a matrix, and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and wherein a compound fillet is disposed at a junction between first and second ones of the walls, the compound fillet including first and second portions, the second portion having a concave curvature extending into the first one of the walls. | 06-20-2013 |
| 20130156557 | SHAPING APPARATUS AND METHOD OF SHAPING A WORKPIECE - A shaping apparatus for shaping a workpiece. The apparatus comprises first and second pairs of shaping members and a spacer located between the first and second pairs of shaping members. The first pair of shaping members comprises a material having a first linear coefficient of thermal expansion, and the second pair of shaping members comprises a material having a third linear coefficient of thermal expansion. The first linear coefficient of thermal expansion is higher than the second linear coefficient of thermal expansion such that on heating of the apparatus, thermal expansion of the shaping members causes the first pair of shaping members to expand outwardly, and the second pair of shaping members to expand inwardly. | 06-20-2013 |
| 20130156558 | ANNULAR GAS TURBINE ENGINE CASE AND METHOD OF MANUFACTURING - The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform. | 06-20-2013 |
| 20130164122 | FASTENER AND FAN ASSEMBLY USING THE SAME - A fan assembly includes a fan including a board defining a number of through hole, a dustproof member attached to an outer surface of the board, and a number of fasteners. The dustproof member defines a number of fixing legs. Each fastener includes a head abutted against a corresponding one of the fixing legs such that the corresponding leg is sandwiched by the head and the outer surface of the board, a pole extending from a side surface of the head to extend into a corresponding one of the holes, a hook extending in the same direction as the pole from an edge of the head, a projection extending toward the pole from a distal end of the hook and engaged with an inner surface of the board opposite to the outer surface. | 06-27-2013 |
| 20130170967 | FAN IMPELLER STRUCTURE - A fan impeller structure includes an annular body. The annular body has a top section and a receiving space. At least one first bending section is formed between the top section and the annular body. At least one recess is formed at the first bending section. At least one flow guide hole is formed between the first bending section and the recess in communication with the receiving space. In operation, the airflow conducted into the receiving space is increased. Moreover, no matter whether the fan impeller structure is clockwise rotated or counterclockwise rotated, the airflow can be conducted into the receiving space through the flow guide hole. Accordingly, the heat dissipation effect will not be affected by the rotational direction of the fan impeller structure. | 07-04-2013 |
| 20130170968 | HEAT DISSIPATING FAN WITH LATERAL AIR INLET AND OUTLET - An exemplary heat dissipating fan includes a frame and an impeller rotatablely received in the frame. The frame includes a base and a top cover disposed on the base, the base includes a bottom plate a peripheral sidewall. The sidewall extends between the bottom plate and the top cover, and the base and the top cover cooperatively defines a receiving space. The impeller is rotatably received in the receiving space. The top cover, the bottom cover and the sidewall cooperatively defines an air inlet therebetween. The top cover, the bottom plate and the sidewall cooperatively defines an outlet therebetween. The air outlet is generally adjacent to and substantially perpendicular to the air inlet. | 07-04-2013 |
| 20130183147 | CENTERING ATTACHMENT OF A COMPRESSOR HOUSING COVER - A casing is provided having a longitudinal axis of a turbomachine, the axis extending along a rotor. The casing includes at least one jacket part extending along the longitudinal axis and at least one end-face cover. The cover is surrounded by the jacket part at least with a part of the axial extension of the cover. In order to reduce the need for radial clearance, without compromising the availability or safety of the operation of the machine, the cover has radial clearance with respect to the jacket part and at least two separate guide elements of the cover are provided on the jacket part in two different circumferential positions with respect to the longitudinal axis. The respective guide elements are designed such that they block a respective movement of the cover in the circumferential direction at least unidirectionally. | 07-18-2013 |
| 20130189089 | VACUUM PUMP - To be provided is a vacuum pump having substrates which can be wired together easily and cooled easily. | 07-25-2013 |
| 20130189090 | VACUUM PUMP - To be provided is a vacuum pump reducing the influence of thermal expansion of connector pins to prevent cracks in soldered parts while preventing damage to electronic elements. | 07-25-2013 |
| 20130216364 | AIRCRAFT PROPULSION SYSTEM NACELLE - An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag. | 08-22-2013 |
| 20130216365 | Fan Unit and Its Mounting - In a method of mounting cooling air fans ( | 08-22-2013 |
| 20130223999 | DUAL-CHAMBER OIL PUMP - An oil pump for a machine is disclosed. The oil pump may have a housing. The oil pump may further have a spacer fixedly connected to the housing. The spacer may divide the housing into a main chamber and an auxiliary chamber. The spacer may also have an opening. The oil pump may further have a drive shaft rotatably disposed within the housing generally orthogonal to the spacer. The drive shaft may pass through the opening. In addition, the oil pump may have a collar fixedly connected to the drive shaft. The collar may be positioned within the opening generally orthogonal to the spacer. The collar may have a diameter of about 2.5 to 3.0 inches and the opening may have a diameter such that an annular gap area between the collar and the spacer is about 0.25 to 0.29 square inches. | 08-29-2013 |
| 20130224000 | Panel for the acoustic treatment comprising hot air ducts and at least one annular channel - An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel. | 08-29-2013 |
| 20130224001 | VACUUM PUMP - The invention relates to a vacuum pump having at least one molecular pump stage, in particular a Holweck stage, which includes a rotor member which forms the pump-active surface of the molecular pump stage and having at least one side channel pump stage which is arranged downstream of the molecular pump stage and which includes a plurality of rotor elements, wherein the rotor elements of the side channel pump stage are supported by the rotor member of the molecular pump stage. The invention further relates to a vacuum pump having at least one molecular pump stage, in particular a Holweck stage, and having at least one side channel pump stage which is arranged downstream of the molecular pump stage and which includes a plurality of rotor elements, wherein the side channel pump stage is arranged between a pump inlet and the molecular pump stage. | 08-29-2013 |
| 20130224002 | COVER HUB WITH SEALING RING - A cover hub for a torque converter includes a radial wall arranged for axial alignment with a cover of the torque converter, a first circumferential surface including an opening for receiving a seal, and a second circumferential surface disposed radially inside of the first circumferential surface and arranged for sealing to a transmission input shaft. The hub has a first fluid passage exiting the hub at a first axial side of the opening and a second fluid passage, circumferentially offset from the first fluid passage and exiting the hub on a second axial side of the opening, opposite the first axial side, and a first circumferential protrusion for sealing the hub to the cover. | 08-29-2013 |
| 20130230391 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - The invention relates to a nacelle ( | 09-05-2013 |
| 20130230392 | AUXILIARY MEMBER FOR ASSEMBLY/DISASSEMBLY OF GAS TURBINE CASING, GAS TURBINE HAVING THE SAME, ASSEMBLY METHOD OF GAS TURBINE CASING, AND DISASSEMBLY METHOD OF GAS TURBINE CASING - An auxiliary member for assembly/disassembly includes a fixing portion which is fixed to one half casing of a lower half casing and an upper half casing, and a jack receiving portion which extends from the fixing portion and faces an outer surface of the other half casing. When an interval between both end portions in the radial direction of the upper half casing is widened due to heat deformation, the fixing portion of the auxiliary member for assembly/disassembly is fixed to the lower half casing, a jack is disposed between the jack receiving portion of the auxiliary member for assembly/disassembly and the outer surface of the upper half casing, and the interval between both end portions of the jack is widened. | 09-05-2013 |
| 20130236300 | HOUSING AND TURBOMACHINE - A housing for a turbomachine includes a peripheral wall delimiting an annular space and a fluid conveying system for redirecting a partial flow of a main flow, which has an axial channel, a front annular channel and a rear annular channel in fluid connection with the axial channel and having a front annular space opening and a rear annular space opening. The fluid conveying system has a front valve device and a rear valve device controllable independently of the front valve device, for opening and closing the annular space openings, and an outlet opening for tapping the partial flow from the fluid conveying system. In the closed state of the rear annular space opening, the partial flow is directable through the rear annular channel and, in the closed state of the front annular space opening, the partial flow is directable through the front annular channel. | 09-12-2013 |
| 20130243582 | COMPRESSOR AND METHOD OF ASSEMBLING THE SAME - A compressor casing to allow easy assemblage and disassembling, a compressor provided with the same, and a method of assembling the compressor are provided. The compressor casing includes a substantially tubular casing, a plurality of sealing surfaces provided on an inner circumferential surface of the casing along an axial direction thereof, a sealing means provided for each sealing surface, a substantially cylindrical bundle for accommodating a blade inside and for being assembled to the casing so as to contact with the sealing surfaces, and a roller provided on an outer circumferential surface of the bundle, for rolling on the inner circumferential surface of the casing when the bundle is assembled to or removed from the casing. The sealing surfaces are connected with one another tapered surfaces. | 09-19-2013 |
| 20130259663 | SIDE SUPPORTED TURBINE SHELL - The present application provides a steam turbine side support system for use with a steam turbine having a rotor. The steam turbine side support system may include a shell for the steam turbine, a number of side support arms extending from the shell in a perpendicular configuration with respect to the rotor, and a foundation in communication with the side support arms. | 10-03-2013 |
| 20130259664 | STRUCTURAL CASE FOR AIRCRAFT GAS TURBINE ENGINE - The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall. | 10-03-2013 |
| 20130259665 | COMPRESSOR - A compressor including: a substantially tubular casing; a substantially cylindrical lid that is provided inside an inner periphery of the casing so as to close off both ends of the casing; a space that is enclosed by the lid and an inner circumferential surface of the casing so as to accommodate a blade; and a seal member that is provided so as to extend in a circumferential direction on the space side of an outer circumferential surface of the lid. A recessed portion, extending inward in the radial direction from the outer circumferential surface of the lid, is provided on the lid at a position between the seal member and the end surface at the space side of the lid. | 10-03-2013 |
| 20130266428 | AXIAL TURBINE WITH CONTAINMENT SHROUD - Various methods and systems are provided for an axial turbine including a containment shroud. In one example, an axial turbine for use in an engine system comprises a turbine disc/blisk and a shroud housing the turbine disc/blisk, the shroud including a first region, a second region, and a third region. A thickness of the second region is dependent on a length between the first region and the third region, and the third region has a burst strength that under a burst condition retains one or more fragments of the turbine disc/blisk. | 10-10-2013 |
| 20130266429 | SPLIT VENTURI RING MAGLEV GENERATOR TURBINE - The present invention is concerned with an improved hydro/aero turbine with a split venturi effect shroud that accelerates the fluid stream through it and boosts the power output, providing a location for energy transfer around its perimeter either by mechanical or electrical means or may have a magnetic ring generator/bearing and other distinctive features that simplify manufacture, assembly, transport, installation and service with the latest technology in direct drive permanent magnet generator. | 10-10-2013 |
| 20130266430 | AIR TURBINE HANDPIECE - An air turbine handpiece having: a head portion with built-in free turbine blade, a neck portion installed consecutively with the head portion and grasped by an operator, a grip portion installed consecutively with the neck portion, an air supply duct for driving the turbine blade, and an exhaust duct for exhausting the air. The exhaust duct is provided with a reflux duct, open at one end to the exhaust duct, and open at the other end to the turbine room as the exhaust exit, a value in which an aperture at the reflux exit of the reflux duct is divided by an aperture in the air supply port of the air supply duct, becomes one or less, and the reflux exit of the reflux duct is opened to the turbine room near the air supply port between the air supply port and the exhaust exit. | 10-10-2013 |
| 20130266431 | METHOD OF FORMING A COMPOSITE STRUCTURE COMPRISING A FLANGE - Method forming a composite structure ( | 10-10-2013 |
| 20130272856 | Swimming Pool Pump Motor Cover - The Stockly Swimming Pool Pump Motor Cover protects both sides; top, and front of the swimming pool pump motor from sun, rain, sprinklers and morning dew. It has an optional base, which secures the top in one place and does not restrict ventilation to the swimming pool pump motor. No tools are required. | 10-17-2013 |
| 20130272857 | METHOD FOR PRODUCING A TURBOCHARGER HOUSING - A method produces a casting, in particular a housing of a turbocharger. Wherein at least one mold part for forming the casting has a respective parting plane which is arranged at a predetermined angle with respect to the longitudinal axis of the casting, and wherein at least one core element is provided. | 10-17-2013 |
| 20130272858 | FAN ASSEMBLY - A fan assembly includes a nozzle and a device for creating an air flow through the nozzle. The nozzle includes an interior passage, a mouth for receiving the air flow from the interior passage, and a Coanda surface located adjacent the mouth and over which the mouth is arranged to direct the air flow. The mouth and the Coanda surface extend about an axis. The Coanda surface comprises a diffuser portion, the angle subtended between the axis and the diffuser portion of the Coanda surface varying about the axis. | 10-17-2013 |
| 20130272859 | Compressor - In a cylinder head ( | 10-17-2013 |
| 20130280050 | TURBINE VIBRATION REDUCTION SYSTEM - A turbine vibration reduction system includes a nozzle, a bucket in operable communication with the nozzle, and a structure having at least one opening configured to inject fluid into flow traveling past the nozzle and the bucket to disrupt formation of a vortex. | 10-24-2013 |
| 20130280051 | FAN ASSEMBLY - A fan assembly includes an annular nozzle and a system for creating a primary air flow. The nozzle includes an outer wall and an inner wall surrounded by the outer wall, the inner wall defining a bore having a bore axis. The nozzle also includes an interior passage located between the inner and outer walls, and extending about the bore axis for receiving an air flow, and an air outlet located at or towards the front of the nozzle for emitting the air flow. The nozzle is configured to emit the air flow through the air outlet in a direction extending away from the bore axis. | 10-24-2013 |
| 20130280052 | NACELLE FOR A BYPASS TURBOFAN ENGINE - A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal. | 10-24-2013 |
| 20130287555 | COMPRESSOR HOUSING BEARING AND SEAL - A compressor housing for an air cycle machine includes an inlet and an outlet. The compressor housing additionally includes a plurality of ribs that extend generally perpendicularly from a surface of the compressor housing. Formed within an internal region of the compressor housing is a bearing support structure. The bearing support structure receives and limits the axial movement of a bearing, seal and at least one O-ring. | 10-31-2013 |
| 20130287556 | TURBINE ASSEMBLY - According to one aspect of the invention, a turbine assembly includes a rotor wheel and a circumferential slot formed in the rotor wheel, the circumferential slot including a uniform cross-section shape for a circumference of the rotor wheel. The assembly also includes a first ring member positioned in the circumferential slot, the first ring member being configured to prevent radial movement of a dovetail attachment when positioned in the circumferential slot, wherein the dovetail attachment is part of a turbine blade. | 10-31-2013 |
| 20130287557 | COMPRESSOR STAKING ARRANGEMENT AND METHOD - A compressor is provided and may include a shell having an inner surface and an outer surface and a bearing housing disposed within the shell and having an engagement surface opposing the inner surface. The engagement surface may include a first channel formed substantially perpendicular to a longitudinal axis of the shell and a second channel formed substantially parallel to the longitudinal axis of the shell and in communication with the first channel. The first channel and the second channel may receive a deformed portion of the shell therein to fix a position of the bearing housing relative to the shell. | 10-31-2013 |
| 20130294901 | METAL POWDER CASTING - A method of component forming according to an exemplary aspect of the present disclosure includes, among other things, positioning a metal powder in a mold cavity, melting the metal powder within the mold cavity, and cooling the melted metal powder to form a component. | 11-07-2013 |
| 20130294902 | Simple device for generating electricity from fluid flows - Trying to save nature and people from pollution and help regenerating nature since using it, power is inexpensive. | 11-07-2013 |
| 20130309074 | SWIVELLING SHIELD PROVIDING PROTECTION TO FAN - A shield for a fan includes a mounting frame, a receiving frame and a mounting plate. A plurality of shielding pieces is pivotally mounted on the mounting frame. The receiving frame receives the mounting frame. The receiving frame includes a bottom edge containing a weight block. The mounting plate defines a vent hole. The receiving frame is pivotally mounted on the mounting plate and aligned to the vent hole. Gravity of the weight block causes the bottom edge to be always in a horizontal direction and the undermost position of the receiving frame. | 11-21-2013 |
| 20130315721 | Exhaust Plenum for Gas Turbine - An exhaust plenum for connection to an exhaust outlet portion of a gas turbine for receiving turbine exhaust gas. The exhaust plenum includes a first wall. The first wall includes a seal attachment component in thermal contact with an exterior shell of the first wall and is adapted for attaching an annular flex seal to the first wall. The seal attachment component extends generally around a perimeter of the inlet of the exhaust plenum, and is thermally insulated from an interior space of the exhaust plenum. | 11-28-2013 |
| 20130315722 | PRESSURE RELEASE SLOT FOR FAN NOISE IMPROVEMENT - A fan shroud includes a body portion and a barrel portion. The body portion and the barrel portion have a first side and a second side. The barrel portion is adjacent to the body portion and defines a cylindrical opening for a fan. The barrel portion and the body portion define a slot in the fan shroud designed to release excess air pressure from the shroud. The slot extends through at least one of the first side and the second side. Any number of slots of different shapes and sizes may be arranged on the fan shroud to reduce noise radiating from the fan shroud. | 11-28-2013 |
| 20130315723 | RING-TYPE FAN AND IMPELLER STRUCTURE THEREOF - A ring-type fan includes a frame having a receiving space defined between an air inlet and an air outlet thereof and being provided along an inner side of the air outlet with an inward projected wall portion; an impeller assembly rotatably mounted in the receiving space and including spaced impellers outward extended from a hub, and a ring member connected to radially outer ends of the impellers and externally provided with a circle of stop section, which and the projected wall portion together define an air passage between them; and at least one pressure relief section defining an airflow guide on the frame to communicate with the receiving space and the air passage. Any backflow can be guided out of the frame via the air passage and the pressure relief section without interfering with the inflow of air, allowing the ring-type fan to have upgraded heat dissipation performance. | 11-28-2013 |
| 20130323037 | ALIGNMENT OF STATIC PARTS IN A GAS TURBINE ENGINE - A first structural static component having an outer diameter is aligned with a second structural static component having an inner diameter to the centerline of a gas turbine engine rotating assembly. The first static component is centered inside the second static component leaving a gap between the outer diameter of the first component and the inner diameter of the second component to permit them to mate at operating temperatures. Tabs and slots are placed on the periphery of the static components to align the static components with the centerline at build temperature. | 12-05-2013 |
| 20130330180 | PASSAGE CHANNEL FOR A TURBOMACHINE AND TURBOMACHINE - A transition duct for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section, including supporting ribs which extend between a radially inner duct wall and a radially outer duct wall and each of which has a profile for deflecting a flow from an inlet area to an outlet area of the transition duct, the supporting ribs each having a profile variation in the area of their trailing edge and/or at least one blow-out opening for blowing out a fluid; also disclosed is a turbomachine having a transition duct of this type. | 12-12-2013 |
| 20130330181 | Pump Housing, in Block Form, of a Vehicle Brake System, and Method for Producing the Same - In a pump housing, in block form, of a vehicle brake system, having a top side which is manufactured to final dimensions and a bottom side which is manufactured to final dimensions, the final dimensions of the top side and of the bottom side are obtained by means of a non-cutting deformation process starting from a blank. | 12-12-2013 |
| 20130336772 | PIPE HAVING AN UPSTREAM CORE HAVING A SHARP CURVATURE - A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region. | 12-19-2013 |
| 20130343883 | TWO-PIECE DUCT ASSEMBLY - A duct assembly for venting flow from an internal portion of a gas turbine engine, has a first piece having a first duct portion extending therethrough, the first piece configured to withstanding backbone loads of the engine, the first piece having a first portion of a duct passing therethrough, and a second piece, the second piece having a second portion of the duct passing therethrough, the second portion and the first portion aligning, the second piece constructed of a lighter material than the first piece. | 12-26-2013 |
| 20140003921 | Remanufactured Pump And Pump Remanufacturing Method | 01-02-2014 |
| 20140003922 | TURBINE EXHAUST CASE DUCT | 01-02-2014 |
| 20140003923 | FUNCTIONALLY GRADED COMPOSITE FAN CONTAINMENT CASE | 01-02-2014 |
| 20140017074 | COMPOSITE MATERIAL PART COMPRISING FIXING MEANS - A fiber structure for reinforcing a composite material part is obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The fiber structure includes fastener elements on at least one of its faces, each fastener element including a body placed under yarns present on a face of the fiber structure, and fastener portions situated over the yarns. | 01-16-2014 |
| 20140030074 | GAS TURBINE ENGINE EXHAUST DUCT - An exhaust duct for a gas turbine engine has an inner wall and an outer wall connected by a plurality of spaced ribs. The duct extends axially. The ribs extend circumferentially across an entire cross-section of the inner and outer walls. The plurality of ribs is spaced axially along the exhaust duct. The inner wall has an inner surface facing an inner chamber. The inner surface receives a coating. The coating is deposited on a metal wire fiber strain isolation pad which is connected to the inner surface. | 01-30-2014 |
| 20140030075 | HOUSING OF COOLING FAN AND METHOD MANUFACTURING OF THE SAME - An exemplary housing of a cooling fan includes a metallic base plate and a plastic bear seat. Clasps extend upwardly from the base plate. The bear seat is formed on the base plate via injection process. A bottom end of the bear seat directly contacts the base plate. The clasps are embedded in the bear seat. | 01-30-2014 |
| 20140037437 | RETROFITABLE AUXILIARY INLET SCOOP - A gas turbine engine includes a fan nacelle and a core nacelle spaced radially inwardly of the fan nacelle to define a bypass flowpath. The engine includes a scoop to direct air from the bypass flowpath into an engine core. The scoop is comprised of a first piece extending outwardly of an outer surface the core nacelle to define an air inlet and a second piece extending inwardly of the core nacelle to define an air outlet. | 02-06-2014 |
| 20140037438 | TURBINE SHROUD FOR A TURBOMACHINE - A turbine shroud includes a body having an upstream edge, a downstream edge, and first and second side edges that collectively define a flowpath surface. A first interface member is arranged on the upstream edge at the first side edge. The first interface member includes a first edge portion having an end portion that extends out at a first non-perpendicular angle relative to the upstream edge and the first side edge from the flowpath surface to a second end portion. A second interface member is arranged on the upstream edge at the second side edge. The second interface member includes an edge section having an end section that extends into at a second non-perpendicular angle relative to the upstream edge and the second side edge the flowpath surface to a second end section. | 02-06-2014 |
| 20140044531 | MOTORHOUSING - An example housing of a cabin air compressor assembly includes a main body portion and a motor outlet duct extending radially from the main body portion. The motor outlet duct interfaces with the main body portion at an interface area. A ratio of a radius of the interface area to an inner diameter of the motor outlet duct is from 0.113 to 0.162. | 02-13-2014 |
| 20140050571 | HARNESS SUPPORT AND MOUNT - A disclosed harness assembly includes a base including a mounting surface and an opening that receives a mount end of a harness clip. A lockable clip is moveable between open and closed positions to secure one or more supply conduits or wire harnesses. The opening of the base includes a securement feature that corresponds with the mount end to hold the harness in a desired orientation relative to the base, to provide a fixed topographical routing. | 02-20-2014 |
| 20140050572 | SOUND ENCLOSURE FOR A COMPRESSOR - A sound enclosure of a compressor to attenuate an operational sound level of the compressor is disclosed. The sound enclosure may be configured to generally enclose the compressor and attenuate radiantly emitted sound by the compressor. The sound enclosure may be configured to include a plurality of assembly sections, particularly two side sections and one bottom section, where the two side sections can be joined together like two halves of a clam shell and joined to the bottom section to facilitate easy assembly. The sound enclosure may form openings at longitudinal ends of the sound enclosure to accommodate refrigerant lines. The assembly sections of the sound enclosure may include one or more openings to accommodate a compressor junction box, wire bundles, oil lines, mounting mechanisms, etc. | 02-20-2014 |
| 20140056699 | Process for Salvaging Turbocharger Compressor Housings - A method of salvaging a used, damaged turbocharger compressor housing involving the steps of machining the damaged interior surface of the housing, grit blasting the machined surface, building up the machined surface with coating material, and final machining the interior surface to its original specifications. The method includes holding the compressor housing by key datums during the machining steps. | 02-27-2014 |
| 20140056700 | COMPRESSOR INLET HOUSING AND METHOD OF MANUFACTURING - A compressor inlet housing includes an aft region having a radially inner surface defining an inner diameter and a radially outer surface defining an outer diameter. Also included is an O-ring groove extending around at least a portion of the aft region within the radially outer surface, the O-ring groove including a groove width, a groove depth and a groove diameter. The O-ring groove also includes an axially forward face, an axially aft face and a circumferential face disposed radially outwardly from the radially inner surface. The compressor inlet housing further includes an O-ring seal simultaneously disposed in contact with the axially forward face, the axially aft face and the circumferential face. | 02-27-2014 |
| 20140056701 | FAN SHROUD WITH COMPLEMENTARY TWO-SIDED RIBBING - A fan shroud has a panel including a first surface and a second surface substantially opposite the first surface. A first rib extends substantially perpendicularly from the first surface, and the first rib has an area of discontinuity where a height of the first rib is reduced. A second rib extends substantially perpendicularly from the second surface, and the second rib is substantially aligned with the first rib and positioned substantially opposite the area of discontinuity of the first rib. | 02-27-2014 |
| 20140064943 | CASING APPARATUS FOR AN AIR PUMP - A casing apparatus for an air pump has a body and a cap. The body has a housing and a combined portion. The housing is composed of a first semi-housing and a second semi-housing. The combined portion is axially formed on and is protruded from a front end of the housing. The cap is rotatably connected with the body and has an inwall a rotating connecter. The rotating connecter protrudes from the inwall and rotatably engages with the combined portion of the body. The cap is mounted on the front end of the housing and combines the first semi-housing with the second semi-housing without any separate securing device such as screws. To form screw holes in the housing is unnecessary. Therefore, the casing apparatus is easy to install and has a low cost. | 03-06-2014 |
| 20140064944 | PRELOAD DISK SPRING, ASSEMBLY STRUCTURE THEREOF, AND FAN USING SAME - A preload disk spring assembly structure for applying a preload to a bearing includes a first and a second main body correspondingly connected to each other face to face. The first main body is provided with at least one first retainer, at least one first notch, and at least one first protruded portion. Similarly, the second main body is provided with at least one second retainer, at least one second notch, and at least one second protruded portion. When the first and the second main body are aligned with each other such that the first retainer is tightly engaged with the second notch, the first notch is tightly engaged with the second retainer and the first protruded portion correspondingly contacts with the second protruded portion, the first and the second main body are brought to assemble together and form an integral body. | 03-06-2014 |
| 20140072418 | FLOATING SEAL - A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value. | 03-13-2014 |
| 20140072419 | ROTARY MACHINES AND METHODS OF ASSEMBLING - A nozzle assembly is provided. The nozzle assembly includes at least one stationary nozzle. An outer ring having a predefined shape includes at least one groove defined therein and the groove is configured to receive at least a portion of the stationary nozzle therein. A coupling portion is formed integrally with the stationary nozzle or the outer ring such that the coupling portion extends outwardly therefrom. An attachment member is coupled to the coupling portion to facilitate substantially restricting movement of the stationary nozzle when the outer ring is substantially distorted. | 03-13-2014 |
| 20140093362 | GAS TURBINE ENGINE COMPONENTS AND METHOD OF ASSEMBLY - An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations. | 04-03-2014 |
| 20140099194 | BIMETALLIC TURBINE SHROUD AND METHOD OF FABRICATING - A bimetallic ring for use as a turbine shroud in a gas turbine engine. The bimetallic ring forms a sealing surface as a hot gas flow path boundary in the engine. The ring is comprised of two materials. The first material, a wrought, oxidation resistant metal alloy comprises a first portion, which is the hot gas flow path sealing surface. The second material, a low cost low alloy steel, comprises a second portion that may be at least a pair of supporting side plates. A dissimilar weld joint joins the sealing surface to the second portion, the at least pair of supporting side plates. | 04-10-2014 |
| 20140099195 | FAN TRAY PERFORATION PATTERN - An apparatus is provided in one example embodiment and includes a plate having a plurality of perforations configured in a pattern. The pattern includes the plurality of perforations arranged in concentric circles centered at a point. Each of the perforations is a closed shape comprising four edges, with rounded corners between adjacent edges, with two opposite edges of each of the perforations including non-parallel straight lines and two other opposite edges comprise concentric, offset curved lines. The non-parallel straight lines may form an angle with a vertex at the point, and the concentric curved lines may be centered at the point. The perforations in each concentric circle may be angularly spaced around the point. The apparatus may further include a substantially circular fan. | 04-10-2014 |
| 20140099196 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 04-10-2014 |
| 20140105735 | LIQUID PUMP DEVICE - The present invention relates to a liquid pump device, comprising a pump shell body, a soft rubber pressing device, a discharge channel, a sealed discharge port end cap, and a guiding tube, wherein the pump shell body comprises an upper shell and a lower shell, wherein the lower shell is provided with an arc surface with an upward opening, the upper shell and the lower shell are connected to form a cavity and the discharge channel communicated with the cavity, and a flange is arranged at the lower end of the arc surface of the lower shell, a through hole being arranged at the middle of the flange; the soft rubber pressing device is snap-fit connected onto the upper shell and covers the cavity, and the soft rubber pressing device forms a cavity with the lower shell; the sealed discharge end cap is provided with at least one cut, the cut forming an invisible discharge port, and the sealed discharge cap is sleeved to an end portion of the discharge channel; and the guiding tube is arranged in the through hole of the flange, and is communicated with the cavity via the feeding channel. The invisible discharge port according to the present invention effectively prevents liquid from contamination caused by ambient environment. | 04-17-2014 |
| 20140105736 | CENTRIFUGAL COMPRESSOR - A centrifugal compressor includes an expanded section which forms a cylindrical space between a suction opening and an impeller. An inlet tapered section is formed on an inlet side of the expanded section, and an outlet tapered section is formed on an outlet side of the expanded section. The expanded section has an inner diameter which is larger than an inner diameter of the suction opening and at least twice as large as an inlet diameter of the impeller. | 04-17-2014 |
| 20140112768 | FORM-FITTING HOUSING COMPONENT COMBINATION AND METHOD FOR THE MANUFACTURE THEREOF - A component combination for a shell of a flow channel ( | 04-24-2014 |
| 20140119904 | IN-SITU PRESSURE ENHANCED PROCESSING OF COMPOSITE ARTICLES - A method for making a composite article comprises securing a layup over a form. The layup including a plurality of dry intermediate reinforcement plies wrapped around an inner reinforcement ply. Resin is infused into the layup under vacuum. The resin-infused layup is consolidated under pressure and cured. | 05-01-2014 |
| 20140133972 | ARRANGEMENT IN WHICH AN INNER CYLINDRICAL CASING IS CONNECTED TO A CONCENTRIC OUTER CYLINDRICAL CASING - An arrangement having inner and outer cylindrical casings connected by a cylindrical connector is presented. The connector is disposed between and concentric with the inner and outer casings and is stiff in direction of concentric axis but flexible in direction radially with respect to concentric axis such that relative thermal expansion of inner and outer cylindrical casings in radial direction is permitted simultaneously maintaining relative position of the casings in axial direction. The connector has annular first and second ends secured to inner and outer casings respectively, and a cylindrical main body between first and second ends flexible in radial direction. The main body has cylindrical first and third sections, annular second section. The first section extends axially away from the first end to a radially inner pat of the second section. The third section extends axially from a radially outer part of the second section towards the second end. | 05-15-2014 |
| 20140140830 | INNER STRUCTURE FOR AN AIRCRAFT NACELLE - An inner structure for a nacelle for an aircraft turbofan includes a plurality of active and passive movable portions. Each active movable portion can drive adjacent passive movable portions such that the inner structure has a nominal first position, a second position and a third position. In the second position, the active movable portions project beyond by the passive movable portions toward the outside of the inner structure after the active mobile portions have driven the passive mobile portions. In the third position, the active movable portions project beyond the passive movable portions toward the inside of the inner structure after the active mobile portions have driven the passive mobile portions. The present disclosure also relates to a nacelle having an outer structure and such an inner structure. | 05-22-2014 |
| 20140140831 | ACTUATING FORCE TRANSMITTING DEVICE OF AN EXHAUST-GAS TURBOCHARGER - An actuating force transmitting device ( | 05-22-2014 |
| 20140154064 | THRUST REVERSER DEVICE - A thrust reverser device of a nacelle includes a thrust reversal cowl which moves alternately from a closed position to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers a flow deflector, and a rear frame supporting deflecting cascades. The flow deflector includes first deflecting cascades distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through the first deflecting cascades, when the thrust reverser device is in reverse jet. In particular, the rear frame has an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet. | 06-05-2014 |
| 20140161599 | ROLLING BEARING ARRANGEMENT OF A SHAFT OF AN EXHAUST-GAS TURBOCHARGER - A rolling bearing arrangement ( | 06-12-2014 |
| 20140178185 | EGRESS SEAL ASSEMBLY - A seal assembly includes a first ferrule that surrounds the lead and a second ferrule that surrounds the lead. | 06-26-2014 |
| 20140178186 | BLOWER FAN - In a blower fan according to a preferred embodiment of the present invention, a side wall portion includes a tongue portion arranged to project between an air outlet and an impeller. A side surface of the tongue portion includes a tongue portion tip arranged to touch a first imaginary plane including a central axis; a first tongue portion side surface arranged to extend from the tongue portion tip along an outer envelope of the impeller; and a second tongue portion side surface arranged to extend from the tongue portion tip toward a side edge, the side edge being a line of intersection of the air outlet and the side wall portion. The second tongue portion side surface is arranged to cross a second imaginary plane including the central axis and touching the side edge. | 06-26-2014 |
| 20140186166 | Hybrid Continuous Fiber Chopped Fiber Polymer Composite Structure - An engine component having a monolithic composite body, the body having a continuous fiber portion, a chopped fiber portion, a thermoplastic polymer contained in both the continuous fiber portion and the chopped fiber portion and between the continuous and chopped fiber portions. | 07-03-2014 |
| 20140186167 | MULTI-PIECE FAIRING FOR MONOLITHIC TURBINE EXHAUST CASE - A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing. | 07-03-2014 |
| 20140186168 | COMPONENT RETENTION WITH PROBE - A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing. | 07-03-2014 |
| 20140234089 | ACTUATING ASSEMBLY FOR A THRUST REVERSER OF AN AIRCRAFT ENGINE - An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even. | 08-21-2014 |
| 20140234090 | REAR NACELLE ASSEMBLY FOR A TURBOJET ENGINE - A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis. | 08-21-2014 |
| 20140255173 | FAN ASSEMBLY - A nozzle for a fan assembly includes an air inlet, an air outlet, an interior passage for conveying air from the air inlet to the air outlet, an annular inner wall, and an outer wall extending about the inner wall. The interior passage is located between the inner wall and the outer wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The air outlet is arranged to direct air over an external surface at least partially defining the bore. A flow control port is located downstream from that surface. A flow control chamber is provided for conveying air to the flow control port. A control mechanism selectively enables a flow of air through the flow control port to deflect an air flow emitted from the air outlet. | 09-11-2014 |
| 20140271155 | MODULAR TURBOMACHINE INLET ASSEMBLY AND RELATED INLET TRANSITION SECTION - An inlet transition section and an inlet bowl entry can be designed to reduce a number of turbomachine casing designs. Using relationships between flow properties, distances between elements, crossover/supply pipe diameter, ideal cross sectional area, aspect ratio, and inlet bowl entry size, a transition from circular cross section to substantially polygonal cross section can be made while enabling adoption of a single size of substantially polygonal inlet bowl entry for a plurality of turbine sizes and/or crossover/supply pipe sizes with minimal losses. | 09-18-2014 |
| 20140271156 | Apparatus for converting wind into circular mechanical motion - Pocket and cup sails formed from flexible materials, especially such sails formed with excess material, have spar like supports attached at their deepest point to maintain the depth of the said sails when the wind fills them so that the sails expand to maximize resistance to the wind coming into the openings of the sails and so that the sails deflate when the wind is coming from the back of the sails to minimize resistance to the wind, the said sails being attached to rotor arms on rotary devices to provide torque, the torque being used to rotate decorative structures including the sails themselves, generate electricity, bring airplane tires up to speed before landing, and/or measure wind speed, and sails optionally having cuffs on the inside to help the sails inflate and/or maintain inflation by minimizing spillage of air. | 09-18-2014 |
| 20140286764 | COMPOSITE PANEL HAVING A BUILT-IN SAMPLING SCOOP - A composite panel includes an inner skin and an outer skin and has an opening for receiving a sampling scoop, which forms a channel and the sampling opening of which is in communication with the outer skin. In particular, the outer skin is shaped such that, at the opening, same forms at least a portion of a flow surface of the sampling scoop. | 09-25-2014 |
| 20140294573 | AXISYMMETRICAL INTERMEDIATE CASE PART INCLUDING AN INSERT POSITIONED IN AN ANNULAR GROOVE - The invention proposes an axisymmetrical portion ( | 10-02-2014 |
| 20140301835 | AIRCRAFT NACELLE ASSEMBLIES - Aircraft nacelles include a frame, a cowl operatively and rotatably coupled to the frame, and a biasing member operatively coupled between the frame and the cowl. The biasing member is configured to assist in the manual opening of the cowl and the manually closing of the cowl. | 10-09-2014 |
| 20140314552 | TURBINE ASSEMBLY FOR A TORQUE CONVERTER INCLUDING A TAB PLATE AND TURBINE SHELL BRAZED TOGETHER AND METHOD OF FORMING - A turbine assembly is provided. The turbine assembly includes a turbine shell and a tab plate connected to the turbine shell, the turbine shell and the tab plate being brazed together. A method of forming a turbine assembly impeller is also provided. The method includes aligning a tab plate with a turbine shell with a braze material therebetween and brazing the tab plate and turbine shell together by melting the braze material. | 10-23-2014 |
| 20140314553 | Method for Manufacturing a Plastic Housing and Plastic Housing - In a method for manufacturing a plastic housing, in particular a compressor housing, by joining at least two contact surfaces of at least two plastic components, the contact surfaces are joined with each other by a hot gas welding process or by an electromagnetic resistance welding process or by a combination of both. | 10-23-2014 |
| 20140314554 | STATOR ELEMENT FOR A HOLWECK PUMP STAGE, VACUUM PUMP HAVING A HOLWECK PUMP STAGE AND METHOD OF MANUFACTURING A STATOR ELEMENT FOR A HOLWECK PUMP STAGE - A stator element for a Holweck pump stage has a base shape of substantially cylinder jacket shape or a kit of parts for a stator element for a Holweck pump stage which has a base shape of a substantially cylinder jacket shape, wherein the stator element or the kit of parts comprises a plurality of stator parts which are separate from one another, which are assembled to form the stator element or can be assembled to form the stator element. A vacuum pump having a Holweck pump stage as well as to a method of manufacturing a stator element for a Holweck pump stage or of manufacturing a kit of parts for a stator element for a Holweck pump stage are also disclosed. | 10-23-2014 |
| 20140321998 | HOUSING SECTION OF A TURBINE ENGINE COMPRESSOR STAGE OR TURBINE ENGINE TURBINE STAGE - A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius. | 10-30-2014 |
| 20140321999 | TURBINE ENGINE CASING - The invention relates to a turbine engine casing comprising a substantially cylindrical wall ( | 10-30-2014 |
| 20150016976 | WIND TURBINE NACELLE - The invention relates to nacelle of a wind turbine. According to the invention, the wind turbine has a tower or mast, an aerodynamic rotor, and a generator having an electric-machine rotor and a stator, and the nacelle is provided with a nacelle covering, wherein the nacelle, in particular the nacelle covering is self-supporting. | 01-15-2015 |
| 20150016977 | ASSEMBLY OF A TURBOMACHINE - A turbomachine and a method for the assembly of the turbomachine with a housing and with a rotor, in which at least one cover of the housing is fastened to the rotor, and the combination is placed into a lower part of the housing and is then enclosed by an upper part of the housing, is provided. To attain centered mounting of the cover assembly and to thus prevent damage to the shaft seal, it is proposed that the combination, as it is placed in, is supported on at least one guide means in the housing, and the guide means forms a guide for the cover in the housing, by means of which guide the placed-in cover is held spaced apart from the housing lower part and the housing upper part with a radial assembly gap. | 01-15-2015 |
| 20150078889 | COMPRESSOR CASING COMPRISING CAVITIES HAVING AN OPTIMISED UPSTREAM SHAPE - A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls. | 03-19-2015 |
| 20150110613 | PROPULSION SYSTEM NACELLE WITH REDUCED NUMBER OF EXTERNAL SPLIT LINES - A cowl for use in a nacelle is provided. The nacelle at least partially surrounds an engine that extends circumferentially about an axially-extending engine centerline. The cowl includes a first side portion and a second side portion. The first and second side portions each are pivotably connected to the nacelle proximate a top of the nacelle. The first and second side portions are configured so that they abut one another to form an external split line proximate the top of the nacelle. | 04-23-2015 |
| 20150308291 | ACCESS PANEL(S) FOR AN INNER NACELLE OF A TURBINE ENGINE - An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least partially cover an aperture in the nacelle wall. The outer nacelle axially overlaps the access panel. | 10-29-2015 |
| 20150330255 | ANTI-TORSION ASSEMBLY WITH WEDGE-SHAPED TORQUE BLOCK - An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes relative movement of the thermally conforming liner and the fan containment case by providing a wedge shaped torque block and complimentary shaped L-brackets. A method of assembling a fan case assembly is also provided. | 11-19-2015 |
| 20150354386 | COOLED FINGER SEAL - An air seal for a gas turbine engine platform comprises a flow path platform, a seal retention ring, a finger seal. The seal retention ring is situated radially adjacent the flow path platform. The finger seal is retained by the seal retention ring between the flow path platform and the seal retention ring. The finger seal comprises a first ply with first keyhole slots, a second ply with second keyhole slots circumferentially offset relative to the first keyhole slots, and a foil layer. The foil layer is disposed between the first and second plies. The finger seal has a series of cooling holes in the outer circumferential segment to cool the outer diameter of the seal. In addition, leakage between the finger seal and the flow path platform cools the inner diameter of the seal. | 12-10-2015 |
| 20150354586 | FAN ASSEMBLY - A bladeless fan assembly for creating an air current includes a nozzle mounted on a base. The nozzle comprises an interior passage and a mouth for receiving the air flow from the interior passage and through which the air flow is emitted from the fan assembly. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The nozzle is detachable from the base, which is preferably sized to be accommodated within the opening of the nozzle for transportation. | 12-10-2015 |
| 20150377070 | Modular Mount Assembly - A mount assembly is described. The mount assembly may comprise a base unit having a surface, an extension unit stacked on and connected to the surface, and a clamp unit stacked on and connected to the extension unit. | 12-31-2015 |
| 20160003101 | COMPONENT - A composite casing comprising a barrel and a stiffening ring provided around the barrel. The stiffening ring includes a section having a waved profile in a circumferential direction. | 01-07-2016 |
| 20160010503 | Instrumentation Boss For Fan Containment Case | 01-14-2016 |
| 20160031316 | TANK AND FILLER TUBE DEVICE WITH PROTECTIVE ARRANGEMENT - A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position. | 02-04-2016 |
| 20160032747 | SEALING ELEMENT FOR SEALING GAP - A sealing element for sealing a gap between two components, which can thermally move relative to each other and each have two substantially parallel component grooves, wherein the sealing element is directed along a main line and has, in a cross section substantially perpendicular to the main line, a first and second end segment and a middle region arranged between the end segments, to ensure an effective seal in the event of thermal expansions of the components that are comparatively large radially and to reduce thermal stresses and crack formations on the components. A third end segment having substantially the same extension direction as the first end segment is arranged on the middle region in parallel with the first end segment and a fourth end segment having substantially the same extension direction as the second end segment is arranged on the middle region in parallel with the second end segment. | 02-04-2016 |
| 20160047275 | COMPOSITE ATTACHMENT STRUCTURE WITH 3D WEAVE - An attachment structure for a case includes a V-groove defined by first and second arms extending circumferentially around the case and meeting at a lower portion. At least a portion of the attachment structure is a three-dimensionally woven composite. | 02-18-2016 |
| 20160083102 | NACELLE - A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface. | 03-24-2016 |
| 20160097290 | ENGINE NACELLE - A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine. | 04-07-2016 |
| 20160101871 | ASSISTANCE DEVICE FOR OPERATING A COWL AND A NACELLE FOR TURBOJET ENGINE EQUIPPED THEREWITH - An assistance device is provided to maneuver of a cover of a nacelle of a turbojet engine. The assistance device includes a joint collinear with an existing joint or hinge for a fitting of the cover, and the joint of the device is rigidly secured to an angled part of which one end bears on the fitting of the cover and of which one point is hinged to a compression spring in order to apply assistance momentum to the fitting of the cover when the cover is raised. | 04-14-2016 |
| 20160102675 | EFFICIENT VACUUM CLEANER FAN INLET - A vacuum comprising a canister and a removable lid assembly that is configured to couple to the canister. The lid assembly includes a motor, an impeller coupled to the motor, a filter mounting structure configured to receive a filter element, and an impeller inlet with curved inner walls. These curved inner walls help to minimize air flow path disruptions. | 04-14-2016 |
| 20160108811 | GAS TURBINE ENGINE NACELLE - A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centreline of the engine. | 04-21-2016 |
| 20160108931 | MOUNTING ARRANGEMENT FOR VARIABLE STATOR VANE - The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths. | 04-21-2016 |
| 20160131156 | Device and System for Eliminating Air Pockets, Eliminating Air Stratification, Minimizing Inconsistent Temperature, and Increasing Internal Air Turns - A device for managing air flow within a volume and/or within the device throw area or range, which includes an air transfer component, an entrance to the device, air induction ports, directional vanes, and three exit zones that incorporate lattices. The device minimizes or eliminates air pockets, air stratification, inconsistent temperature, and increases interior air turns within the volume of air to be managed. | 05-12-2016 |
| 20160138414 | ACCESSORY DRIVE CASE FOR A TURBOPROP - A turbomachine including an accessory drive case, connected to the engine shaft via a radial shaft, wherein the accessory drive case also includes: a primary shaft which is driven by the radial shaft via a bevel gearbox, and assemblies for mechanically driving accessories, driven by the primary shaft and configured such that the related accessories lie at the upper portion and on at least one of the side edges of the engine case. | 05-19-2016 |
| 20160143504 | DISHWASHER DRAIN ASSEMBLIES HAVING OVERMOLDED VOLUTES - Dishwasher drain assemblies having overmolded volutes are disclosed. A disclosed example drain assembly for a dishwasher having a tub, a sump fluidly coupled to the tub, and a discharge outlet includes a drain pump having an impeller to pump fluid from the sump to the discharge outlet, and a resilient member overmolded onto at least a portion of the drain pump, the resilient member defining a volute for the drain pump. | 05-26-2016 |
| 20160146049 | SEALING INTERFACE FOR A CASE OF A GAS TURBINE ENGINE - A case assembly for a gas turbine engine, includes a case with an oversized case boss, said oversized case boss including a peripheral wall that defines a first inner diameter in a first condition to receive a piston seal, and a second inner diameter in a second condition, the second condition including enlargement of the first inner diameter to form a second inner diameter and a bushing mounted within the second inner diameter, an inner diameter of the bushing defines a bushing inner diameter about equivalent to the first inner diameter to receive the piston seal. | 05-26-2016 |
| 20160153313 | FLANGE PARTIAL SECTION REPLACEMENT REPAIR | 06-02-2016 |
| 20160153315 | MOMENT ACCOMMODATING FASTENER ASSEMBLY | 06-02-2016 |
| 20160177788 | INTERGRATED SEAL SUPPORTS | 06-23-2016 |
| 20160201566 | LARGE DISPLACEMENT HIGH TEMPERATURE SEAL | 07-14-2016 |
| 20160376905 | SEALING SYSTEM FOR A STEAM TURBINE, AND STEAM TURBINE - A sealing system for sealing a sealing gap between an outer housing and a rotor shaft of a rotor of a steam turbine, having a blocking medium wall for producing a blocking medium area between the rotor shaft and the outer housing in the region in front of and/or in the sealing gap, wherein the blocking medium wall is secured to the outer housing. The sealing system also has a blocking medium opening in the blocking medium wall in order to feed a blocking medium from the outside into the blocking medium area. The sealing system also has a shaft seal for sealing the blocking medium area from a second area, which has a second pressure that is lower than the first pressure, and a sliding ring seal for sealing the blocking medium area from a third area, which has a third pressure that is lower than the second pressure. | 12-29-2016 |
| 20160376925 | SEAL SUPPORT STRUCTURES FOR TURBOMACHINES - A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion. | 12-29-2016 |
